

Weapon Aircraft/Heavy Metal/B747-400 United/Weapons:flaptrack 4 B.wpn:

The frontal area                is    0.533 square meters.
The side area                   is    2.155 square meters.
The top area                    is    1.997 square meters.
The wetted area                 is    7.582 square meters.
The longitudinal centroid       is    0.907 meters from the CG OF THE WEAPON.
The lateral      centroid       is    0.000 meters from the CG OF THE WEAPON.
The vertical     centroid       is   -0.183 meters from the CG OF THE WEAPON.
The radius of gyration in roll  is    0.42 meters.
The radius of gyration in pitch is    1.28 meters.
The radius of gyration in yaw   is    1.26 meters.



Weapon Aircraft/Heavy Metal/B747-400 United/Weapons:flaptrack 4 B.wpn:

The frontal area                is    0.533 square meters.
The side area                   is    2.155 square meters.
The top area                    is    1.997 square meters.
The wetted area                 is    7.582 square meters.
The longitudinal centroid       is    0.907 meters from the CG OF THE WEAPON.
The lateral      centroid       is    0.000 meters from the CG OF THE WEAPON.
The vertical     centroid       is   -0.183 meters from the CG OF THE WEAPON.
The radius of gyration in roll  is    0.42 meters.
The radius of gyration in pitch is    1.28 meters.
The radius of gyration in yaw   is    1.26 meters.



Weapon Aircraft/Heavy Metal/B747-400 United/Weapons:flaptrack 3 B.wpn:

The frontal area                is    0.546 square meters.
The side area                   is    2.643 square meters.
The top area                    is    2.169 square meters.
The wetted area                 is    8.796 square meters.
The longitudinal centroid       is    1.054 meters from the CG OF THE WEAPON.
The lateral      centroid       is    0.000 meters from the CG OF THE WEAPON.
The vertical     centroid       is   -0.234 meters from the CG OF THE WEAPON.
The radius of gyration in roll  is    0.45 meters.
The radius of gyration in pitch is    1.46 meters.
The radius of gyration in yaw   is    1.43 meters.



Weapon Aircraft/Heavy Metal/B747-400 United/Weapons:flaptrack 3 B.wpn:

The frontal area                is    0.546 square meters.
The side area                   is    2.643 square meters.
The top area                    is    2.169 square meters.
The wetted area                 is    8.796 square meters.
The longitudinal centroid       is    1.054 meters from the CG OF THE WEAPON.
The lateral      centroid       is    0.000 meters from the CG OF THE WEAPON.
The vertical     centroid       is   -0.234 meters from the CG OF THE WEAPON.
The radius of gyration in roll  is    0.45 meters.
The radius of gyration in pitch is    1.46 meters.
The radius of gyration in yaw   is    1.43 meters.



Weapon Aircraft/Heavy Metal/B747-400 United/Weapons:flaptrack 2 B.wpn:

The frontal area                is    0.535 square meters.
The side area                   is    3.071 square meters.
The top area                    is    2.579 square meters.
The wetted area                 is   10.350 square meters.
The longitudinal centroid       is    1.403 meters from the CG OF THE WEAPON.
The lateral      centroid       is    0.000 meters from the CG OF THE WEAPON.
The vertical     centroid       is   -0.209 meters from the CG OF THE WEAPON.
The radius of gyration in roll  is    0.43 meters.
The radius of gyration in pitch is    1.83 meters.
The radius of gyration in yaw   is    1.81 meters.



Weapon Aircraft/Heavy Metal/B747-400 United/Weapons:flaptrack 2 B.wpn:

The frontal area                is    0.535 square meters.
The side area                   is    3.071 square meters.
The top area                    is    2.579 square meters.
The wetted area                 is   10.350 square meters.
The longitudinal centroid       is    1.403 meters from the CG OF THE WEAPON.
The lateral      centroid       is    0.000 meters from the CG OF THE WEAPON.
The vertical     centroid       is   -0.209 meters from the CG OF THE WEAPON.
The radius of gyration in roll  is    0.43 meters.
The radius of gyration in pitch is    1.83 meters.
The radius of gyration in yaw   is    1.81 meters.



Weapon Aircraft/Heavy Metal/B747-400 United/Weapons:flaptrack 1 B.wpn:

The frontal area                is    0.557 square meters.
The side area                   is    3.870 square meters.
The top area                    is    2.946 square meters.
The wetted area                 is   12.378 square meters.
The longitudinal centroid       is    1.613 meters from the CG OF THE WEAPON.
The lateral      centroid       is    0.000 meters from the CG OF THE WEAPON.
The vertical     centroid       is   -0.232 meters from the CG OF THE WEAPON.
The radius of gyration in roll  is    0.45 meters.
The radius of gyration in pitch is    2.10 meters.
The radius of gyration in yaw   is    2.08 meters.



Weapon Aircraft/Heavy Metal/B747-400 United/Weapons:flaptrack 1 B.wpn:

The frontal area                is    0.557 square meters.
The side area                   is    3.870 square meters.
The top area                    is    2.946 square meters.
The wetted area                 is   12.378 square meters.
The longitudinal centroid       is    1.613 meters from the CG OF THE WEAPON.
The lateral      centroid       is    0.000 meters from the CG OF THE WEAPON.
The vertical     centroid       is   -0.232 meters from the CG OF THE WEAPON.
The radius of gyration in roll  is    0.45 meters.
The radius of gyration in pitch is    2.10 meters.
The radius of gyration in yaw   is    2.08 meters.



Weapon Aircraft/Heavy Metal/B747-400 United/Weapons:flaptrack 1 F.wpn:

The frontal area                is    0.410 square meters.
The side area                   is    1.382 square meters.
The top area                    is    1.465 square meters.
The wetted area                 is    5.501 square meters.
The longitudinal centroid       is   -0.921 meters from the CG OF THE WEAPON.
The lateral      centroid       is    0.000 meters from the CG OF THE WEAPON.
The vertical     centroid       is   -0.171 meters from the CG OF THE WEAPON.
The radius of gyration in roll  is    0.34 meters.
The radius of gyration in pitch is    1.22 meters.
The radius of gyration in yaw   is    1.21 meters.



Weapon Aircraft/Heavy Metal/B747-400 United/Weapons:flaptrack 1 F.wpn:

The frontal area                is    0.410 square meters.
The side area                   is    1.382 square meters.
The top area                    is    1.465 square meters.
The wetted area                 is    5.501 square meters.
The longitudinal centroid       is   -0.921 meters from the CG OF THE WEAPON.
The lateral      centroid       is    0.000 meters from the CG OF THE WEAPON.
The vertical     centroid       is   -0.171 meters from the CG OF THE WEAPON.
The radius of gyration in roll  is    0.34 meters.
The radius of gyration in pitch is    1.22 meters.
The radius of gyration in yaw   is    1.21 meters.



Weapon Aircraft/Heavy Metal/B747-400 United/Weapons:flaptrack 2 F.wpn:

The frontal area                is    0.416 square meters.
The side area                   is    1.782 square meters.
The top area                    is    1.870 square meters.
The wetted area                 is    6.927 square meters.
The longitudinal centroid       is   -1.039 meters from the CG OF THE WEAPON.
The lateral      centroid       is    0.000 meters from the CG OF THE WEAPON.
The vertical     centroid       is   -0.175 meters from the CG OF THE WEAPON.
The radius of gyration in roll  is    0.35 meters.
The radius of gyration in pitch is    1.44 meters.
The radius of gyration in yaw   is    1.43 meters.



Weapon Aircraft/Heavy Metal/B747-400 United/Weapons:flaptrack 2 F.wpn:

The frontal area                is    0.416 square meters.
The side area                   is    1.782 square meters.
The top area                    is    1.870 square meters.
The wetted area                 is    6.927 square meters.
The longitudinal centroid       is   -1.039 meters from the CG OF THE WEAPON.
The lateral      centroid       is    0.000 meters from the CG OF THE WEAPON.
The vertical     centroid       is   -0.175 meters from the CG OF THE WEAPON.
The radius of gyration in roll  is    0.35 meters.
The radius of gyration in pitch is    1.44 meters.
The radius of gyration in yaw   is    1.43 meters.



Weapon Aircraft/Heavy Metal/B747-400 United/Weapons:flaptrack 4 F.wpn:

The frontal area                is    0.436 square meters.
The side area                   is    1.322 square meters.
The top area                    is    1.346 square meters.
The wetted area                 is    5.178 square meters.
The longitudinal centroid       is   -0.277 meters from the CG OF THE WEAPON.
The lateral      centroid       is    0.000 meters from the CG OF THE WEAPON.
The vertical     centroid       is   -0.151 meters from the CG OF THE WEAPON.
The radius of gyration in roll  is    0.35 meters.
The radius of gyration in pitch is    0.79 meters.
The radius of gyration in yaw   is    0.77 meters.



Weapon Aircraft/Heavy Metal/B747-400 United/Weapons:flaptrack 4 F.wpn:

The frontal area                is    0.436 square meters.
The side area                   is    1.322 square meters.
The top area                    is    1.346 square meters.
The wetted area                 is    5.178 square meters.
The longitudinal centroid       is   -0.277 meters from the CG OF THE WEAPON.
The lateral      centroid       is    0.000 meters from the CG OF THE WEAPON.
The vertical     centroid       is   -0.151 meters from the CG OF THE WEAPON.
The radius of gyration in roll  is    0.35 meters.
The radius of gyration in pitch is    0.79 meters.
The radius of gyration in yaw   is    0.77 meters.



Weapon Aircraft/Heavy Metal/B747-400 United/Weapons:flaptrack 3 F.wpn:

The frontal area                is    0.428 square meters.
The side area                   is    1.036 square meters.
The top area                    is    1.116 square meters.
The wetted area                 is    4.244 square meters.
The longitudinal centroid       is   -0.571 meters from the CG OF THE WEAPON.
The lateral      centroid       is    0.000 meters from the CG OF THE WEAPON.
The vertical     centroid       is   -0.149 meters from the CG OF THE WEAPON.
The radius of gyration in roll  is    0.34 meters.
The radius of gyration in pitch is    0.84 meters.
The radius of gyration in yaw   is    0.83 meters.



Weapon Aircraft/Heavy Metal/B747-400 United/Weapons:flaptrack 3 F.wpn:

The frontal area                is    0.428 square meters.
The side area                   is    1.036 square meters.
The top area                    is    1.116 square meters.
The wetted area                 is    4.244 square meters.
The longitudinal centroid       is   -0.571 meters from the CG OF THE WEAPON.
The lateral      centroid       is    0.000 meters from the CG OF THE WEAPON.
The vertical     centroid       is   -0.149 meters from the CG OF THE WEAPON.
The radius of gyration in roll  is    0.34 meters.
The radius of gyration in pitch is    0.84 meters.
The radius of gyration in yaw   is    0.83 meters.



Weapon Aircraft/Heavy Metal/B747-400 United/Weapons:LG outer.wpn:

The frontal area                is    0.082 square meters.
The side area                   is    0.415 square meters.
The top area                    is    0.529 square meters.
The wetted area                 is    2.232 square meters.
The longitudinal centroid       is    0.704 meters from the CG OF THE WEAPON.
The lateral      centroid       is    0.000 meters from the CG OF THE WEAPON.
The vertical     centroid       is   -0.121 meters from the CG OF THE WEAPON.
The radius of gyration in roll  is    0.28 meters.
The radius of gyration in pitch is    0.79 meters.
The radius of gyration in yaw   is    0.75 meters.



Weapon Aircraft/Heavy Metal/B747-400 United/Weapons:LG outer.wpn:

The frontal area                is    0.082 square meters.
The side area                   is    0.415 square meters.
The top area                    is    0.529 square meters.
The wetted area                 is    2.232 square meters.
The longitudinal centroid       is    0.704 meters from the CG OF THE WEAPON.
The lateral      centroid       is    0.000 meters from the CG OF THE WEAPON.
The vertical     centroid       is   -0.121 meters from the CG OF THE WEAPON.
The radius of gyration in roll  is    0.28 meters.
The radius of gyration in pitch is    0.79 meters.
The radius of gyration in yaw   is    0.75 meters.



Weapon Aircraft/Heavy Metal/B747-400 United/Weapons:Pitot Tube long.wpn:

The frontal area                is    0.006 square meters.
The side area                   is    0.036 square meters.
The top area                    is    0.023 square meters.
The wetted area                 is    0.116 square meters.
The longitudinal centroid       is   -0.143 meters from the CG OF THE WEAPON.
The lateral      centroid       is    0.000 meters from the CG OF THE WEAPON.
The vertical     centroid       is   -0.038 meters from the CG OF THE WEAPON.
The radius of gyration in roll  is    0.07 meters.
The radius of gyration in pitch is    0.19 meters.
The radius of gyration in yaw   is    0.18 meters.



Weapon Aircraft/Heavy Metal/B747-400 United/Weapons:Pitot Tube short.wpn:

The frontal area                is    0.006 square meters.
The side area                   is    0.033 square meters.
The top area                    is    0.019 square meters.
The wetted area                 is    0.105 square meters.
The longitudinal centroid       is   -0.112 meters from the CG OF THE WEAPON.
The lateral      centroid       is    0.000 meters from the CG OF THE WEAPON.
The vertical     centroid       is   -0.042 meters from the CG OF THE WEAPON.
The radius of gyration in roll  is    0.07 meters.
The radius of gyration in pitch is    0.16 meters.
The radius of gyration in yaw   is    0.14 meters.



Weapon Aircraft/Heavy Metal/B747-400 United/Weapons:Pitot Tube long.wpn:

The frontal area                is    0.006 square meters.
The side area                   is    0.036 square meters.
The top area                    is    0.023 square meters.
The wetted area                 is    0.116 square meters.
The longitudinal centroid       is   -0.143 meters from the CG OF THE WEAPON.
The lateral      centroid       is    0.000 meters from the CG OF THE WEAPON.
The vertical     centroid       is   -0.038 meters from the CG OF THE WEAPON.
The radius of gyration in roll  is    0.07 meters.
The radius of gyration in pitch is    0.19 meters.
The radius of gyration in yaw   is    0.18 meters.



Weapon Aircraft/Heavy Metal/B747-400 United/Weapons:Pitot Tube short.wpn:

The frontal area                is    0.006 square meters.
The side area                   is    0.033 square meters.
The top area                    is    0.019 square meters.
The wetted area                 is    0.105 square meters.
The longitudinal centroid       is   -0.112 meters from the CG OF THE WEAPON.
The lateral      centroid       is    0.000 meters from the CG OF THE WEAPON.
The vertical     centroid       is   -0.042 meters from the CG OF THE WEAPON.
The radius of gyration in roll  is    0.07 meters.
The radius of gyration in pitch is    0.16 meters.
The radius of gyration in yaw   is    0.14 meters.



Weapon Aircraft/Heavy Metal/B747-400 United/Weapons:Wing Root.wpn:

The frontal area                is    0.133 square meters.
The side area                   is    5.004 square meters.
The top area                    is    5.750 square meters.
The wetted area                 is   15.781 square meters.
The longitudinal centroid       is    6.603 meters from the CG OF THE WEAPON.
The lateral      centroid       is    0.000 meters from the CG OF THE WEAPON.
The vertical     centroid       is    0.431 meters from the CG OF THE WEAPON.
The radius of gyration in roll  is    0.55 meters.
The radius of gyration in pitch is    7.38 meters.
The radius of gyration in yaw   is    7.36 meters.



Weapon Aircraft/Heavy Metal/B747-400 United/Weapons:Wing Root.wpn:

The frontal area                is    0.133 square meters.
The side area                   is    5.004 square meters.
The top area                    is    5.750 square meters.
The wetted area                 is   15.781 square meters.
The longitudinal centroid       is    6.603 meters from the CG OF THE WEAPON.
The lateral      centroid       is    0.000 meters from the CG OF THE WEAPON.
The vertical     centroid       is    0.431 meters from the CG OF THE WEAPON.
The radius of gyration in roll  is    0.55 meters.
The radius of gyration in pitch is    7.38 meters.
The radius of gyration in yaw   is    7.36 meters.


X-Plane, by Austin Meyer
Simulating Aircraft/Heavy Metal/B747-400 United/United-Air.acf


x location positive aft   x force positive right pitch/alpha pos nose up
y location positive right y force positive up    roll pos right
z location positive up    z force positive aft   yaw/beta pos nose right

elevator, aileron, spoiler   positive control surface up
rudder                       positive control surface right
drag-yaw                     positive control surface deployed
pitch cyclic prop pitch      positive request nose up
roll  cyclic prop pitch      positive request nose right

Finite-Wing & Element Build-Up for LEFT WING 1 :
	root lo Re: alphamax=  16.00 deg, trat= 0.1200, Re= 0.0000 meg for Boeing Root (high subsonic).afl.
	root hi Re: alphamax=  16.00 deg, trat= 0.1200, Re=99.9000 meg for Boeing Root (high subsonic).afl.
	tip  lo Re: alphamax=  16.00 deg, trat= 0.1000, Re= 0.0000 meg for Boeing Mid (high subsonic).afl.
	tip  hi Re: alphamax=  16.00 deg, trat= 0.1000, Re=99.9000 meg for Boeing Mid (high subsonic).afl.
	Element # 1: S=  18.218 sqr mtrs, MAC=  16.16 mtrs, incidence=   3.00 deg.
	Element # 2: S=  17.473 sqr mtrs, MAC=  15.50 mtrs, incidence=   3.50 deg.
	Element # 3: S=  16.727 sqr mtrs, MAC=  14.84 mtrs, incidence=   4.00 deg.
	Element # 4: S=  15.981 sqr mtrs, MAC=  14.18 mtrs, incidence=   4.00 deg.
	Element # 5: S=  15.235 sqr mtrs, MAC=  13.52 mtrs, incidence=   3.80 deg.
	Element # 6: S=  14.490 sqr mtrs, MAC=  12.85 mtrs, incidence=   3.60 deg.
	Element # 7: S=  13.744 sqr mtrs, MAC=  12.19 mtrs, incidence=   3.40 deg.
	Element # 8: S=  12.998 sqr mtrs, MAC=  11.53 mtrs, incidence=   3.30 deg.
	Element # 9: S=  12.253 sqr mtrs, MAC=  10.87 mtrs, incidence=   3.00 deg.
	Element #10: S=  11.507 sqr mtrs, MAC=  10.21 mtrs, incidence=   2.80 deg.
	NOTE! I AM JOINING LEFT WING 1  TO LEFT WING 2  (through any intermediate wings) TO FORM ONE CONTINUOUS WING!
	NOTE! I AM JOINING LEFT WING 1  TO LEFT WING 3  (through any intermediate wings) TO FORM ONE CONTINUOUS WING!
	NOTE! I AM JOINING LEFT WING 1  TO LEFT WING 4  (through any intermediate wings) TO FORM ONE CONTINUOUS WING!
	NOTE! I AM JOINING LEFT WING 1  TO MISC WING 7  (through any intermediate wings) TO FORM ONE CONTINUOUS WING!
	After any wing-joining, our semi-length        is    40.75 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our root chord         is    16.49 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our tip chord          is     1.28 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our leading-edge sweep is    43.92 deg.  (for purposes of                        Delta-Wing factor determination only)
	After any wing-joining, our mean aero	 sweep is    40.07 deg.  (for purposes of Oswalds Efficiency                       determination only)
	After any wing-joining, our aspect ratio       is     7.05.      (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our taper ratio        is     0.08.      (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our washout            is     3.00 deg.  (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root=    3.00 deg, tip=    0.00 deg)
	Oswalds efficiency is therefore  0.9502, for lift-slope reduction to 78.61% of the 2-D value.
	We will accomplish this by:
		using coefficient data at an angle of attack that is 84.99% of actual (stall alpha=  18.83 deg),
		and reducing airfoil lift coefficients to            92.49% of their 2-D value.
		Based on AR and sweep, cm change is to               48.12% of the 2-D value.
		Based on AR and TR, aerodynamic center is moved      19.34% of the way from the the 25% chord to the 50% chord.

Finite-Wing & Element Build-Up for RIGT WING 1 :
	root lo Re: alphamax=  16.00 deg, trat= 0.1200, Re= 0.0000 meg for Boeing Root (high subsonic).afl.
	root hi Re: alphamax=  16.00 deg, trat= 0.1200, Re=99.9000 meg for Boeing Root (high subsonic).afl.
	tip  lo Re: alphamax=  16.00 deg, trat= 0.1000, Re= 0.0000 meg for Boeing Mid (high subsonic).afl.
	tip  hi Re: alphamax=  16.00 deg, trat= 0.1000, Re=99.9000 meg for Boeing Mid (high subsonic).afl.
	Element # 1: S=  18.218 sqr mtrs, MAC=  16.16 mtrs, incidence=   3.00 deg.
	Element # 2: S=  17.473 sqr mtrs, MAC=  15.50 mtrs, incidence=   3.50 deg.
	Element # 3: S=  16.727 sqr mtrs, MAC=  14.84 mtrs, incidence=   4.00 deg.
	Element # 4: S=  15.981 sqr mtrs, MAC=  14.18 mtrs, incidence=   4.00 deg.
	Element # 5: S=  15.235 sqr mtrs, MAC=  13.52 mtrs, incidence=   3.80 deg.
	Element # 6: S=  14.490 sqr mtrs, MAC=  12.85 mtrs, incidence=   3.60 deg.
	Element # 7: S=  13.744 sqr mtrs, MAC=  12.19 mtrs, incidence=   3.40 deg.
	Element # 8: S=  12.998 sqr mtrs, MAC=  11.53 mtrs, incidence=   3.30 deg.
	Element # 9: S=  12.253 sqr mtrs, MAC=  10.87 mtrs, incidence=   3.00 deg.
	Element #10: S=  11.507 sqr mtrs, MAC=  10.21 mtrs, incidence=   2.80 deg.
	NOTE! I AM JOINING RIGT WING 1  TO RIGT WING 2  (through any intermediate wings) TO FORM ONE CONTINUOUS WING!
	NOTE! I AM JOINING RIGT WING 1  TO RIGT WING 3  (through any intermediate wings) TO FORM ONE CONTINUOUS WING!
	NOTE! I AM JOINING RIGT WING 1  TO RIGT WING 4  (through any intermediate wings) TO FORM ONE CONTINUOUS WING!
	NOTE! I AM JOINING RIGT WING 1  TO MISC WING 8  (through any intermediate wings) TO FORM ONE CONTINUOUS WING!
	After any wing-joining, our semi-length        is    40.75 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our root chord         is    16.49 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our tip chord          is     1.28 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our leading-edge sweep is    43.92 deg.  (for purposes of                        Delta-Wing factor determination only)
	After any wing-joining, our mean aero	 sweep is    40.06 deg.  (for purposes of Oswalds Efficiency                       determination only)
	After any wing-joining, our aspect ratio       is     7.05.      (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our taper ratio        is     0.08.      (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our washout            is     3.00 deg.  (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root=    3.00 deg, tip=    0.00 deg)
	Oswalds efficiency is therefore  0.9502, for lift-slope reduction to 78.61% of the 2-D value.
	We will accomplish this by:
		using coefficient data at an angle of attack that is 84.99% of actual (stall alpha=  18.83 deg),
		and reducing airfoil lift coefficients to            92.49% of their 2-D value.
		Based on AR and sweep, cm change is to               48.13% of the 2-D value.
		Based on AR and TR, aerodynamic center is moved      19.33% of the way from the the 25% chord to the 50% chord.

Finite-Wing & Element Build-Up for LEFT WING 2 :
	root lo Re: alphamax=  16.00 deg, trat= 0.1000, Re= 0.0000 meg for Boeing Mid (high subsonic).afl.
	root hi Re: alphamax=  16.00 deg, trat= 0.1000, Re=99.9000 meg for Boeing Mid (high subsonic).afl.
	tip  lo Re: alphamax=  16.00 deg, trat= 0.1000, Re= 0.0000 meg for Boeing Mid (high subsonic).afl.
	tip  hi Re: alphamax=  16.00 deg, trat= 0.1000, Re=99.9000 meg for Boeing Mid (high subsonic).afl.
	Element # 1: S=   4.393 sqr mtrs, MAC=   9.74 mtrs, incidence=   2.80 deg.
	Element # 2: S=   4.273 sqr mtrs, MAC=   9.48 mtrs, incidence=   2.80 deg.
	Element # 3: S=   4.152 sqr mtrs, MAC=   9.21 mtrs, incidence=   2.80 deg.
	Element # 4: S=   4.032 sqr mtrs, MAC=   8.94 mtrs, incidence=   2.80 deg.
	NOTE! I AM JOINING LEFT WING 2  TO LEFT WING 1  (through any intermediate wings) TO FORM ONE CONTINUOUS WING!
	NOTE! I AM JOINING LEFT WING 2  TO LEFT WING 3  (through any intermediate wings) TO FORM ONE CONTINUOUS WING!
	NOTE! I AM JOINING LEFT WING 2  TO LEFT WING 4  (through any intermediate wings) TO FORM ONE CONTINUOUS WING!
	NOTE! I AM JOINING LEFT WING 2  TO MISC WING 7  (through any intermediate wings) TO FORM ONE CONTINUOUS WING!
	After any wing-joining, our semi-length        is    40.75 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our root chord         is    16.49 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our tip chord          is     1.28 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our leading-edge sweep is    43.92 deg.  (for purposes of                        Delta-Wing factor determination only)
	After any wing-joining, our mean aero	 sweep is    40.07 deg.  (for purposes of Oswalds Efficiency                       determination only)
	After any wing-joining, our aspect ratio       is     7.05.      (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our taper ratio        is     0.08.      (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our washout            is     3.00 deg.  (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root=    3.00 deg, tip=    0.00 deg)
	Oswalds efficiency is therefore  0.9502, for lift-slope reduction to 78.61% of the 2-D value.
	We will accomplish this by:
		using coefficient data at an angle of attack that is 84.99% of actual (stall alpha=  18.83 deg),
		and reducing airfoil lift coefficients to            92.49% of their 2-D value.
		Based on AR and sweep, cm change is to               48.12% of the 2-D value.
		Based on AR and TR, aerodynamic center is moved      19.34% of the way from the the 25% chord to the 50% chord.

Finite-Wing & Element Build-Up for RIGT WING 2 :
	root lo Re: alphamax=  16.00 deg, trat= 0.1000, Re= 0.0000 meg for Boeing Mid (high subsonic).afl.
	root hi Re: alphamax=  16.00 deg, trat= 0.1000, Re=99.9000 meg for Boeing Mid (high subsonic).afl.
	tip  lo Re: alphamax=  16.00 deg, trat= 0.1000, Re= 0.0000 meg for Boeing Mid (high subsonic).afl.
	tip  hi Re: alphamax=  16.00 deg, trat= 0.1000, Re=99.9000 meg for Boeing Mid (high subsonic).afl.
	Element # 1: S=   4.393 sqr mtrs, MAC=   9.74 mtrs, incidence=   2.80 deg.
	Element # 2: S=   4.273 sqr mtrs, MAC=   9.48 mtrs, incidence=   2.80 deg.
	Element # 3: S=   4.152 sqr mtrs, MAC=   9.21 mtrs, incidence=   2.80 deg.
	Element # 4: S=   4.032 sqr mtrs, MAC=   8.94 mtrs, incidence=   2.80 deg.
	NOTE! I AM JOINING RIGT WING 2  TO RIGT WING 1  (through any intermediate wings) TO FORM ONE CONTINUOUS WING!
	NOTE! I AM JOINING RIGT WING 2  TO RIGT WING 3  (through any intermediate wings) TO FORM ONE CONTINUOUS WING!
	NOTE! I AM JOINING RIGT WING 2  TO RIGT WING 4  (through any intermediate wings) TO FORM ONE CONTINUOUS WING!
	NOTE! I AM JOINING RIGT WING 2  TO MISC WING 8  (through any intermediate wings) TO FORM ONE CONTINUOUS WING!
	After any wing-joining, our semi-length        is    40.75 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our root chord         is    16.49 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our tip chord          is     1.28 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our leading-edge sweep is    43.92 deg.  (for purposes of                        Delta-Wing factor determination only)
	After any wing-joining, our mean aero	 sweep is    40.06 deg.  (for purposes of Oswalds Efficiency                       determination only)
	After any wing-joining, our aspect ratio       is     7.05.      (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our taper ratio        is     0.08.      (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our washout            is     3.00 deg.  (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root=    3.00 deg, tip=    0.00 deg)
	Oswalds efficiency is therefore  0.9502, for lift-slope reduction to 78.61% of the 2-D value.
	We will accomplish this by:
		using coefficient data at an angle of attack that is 84.99% of actual (stall alpha=  18.83 deg),
		and reducing airfoil lift coefficients to            92.49% of their 2-D value.
		Based on AR and sweep, cm change is to               48.13% of the 2-D value.
		Based on AR and TR, aerodynamic center is moved      19.33% of the way from the the 25% chord to the 50% chord.

Finite-Wing & Element Build-Up for LEFT WING 3 :
	root lo Re: alphamax=  16.00 deg, trat= 0.1000, Re= 0.0000 meg for Boeing Mid (high subsonic).afl.
	root hi Re: alphamax=  16.00 deg, trat= 0.1000, Re=99.9000 meg for Boeing Mid (high subsonic).afl.
	tip  lo Re: alphamax=  16.00 deg, trat= 0.1000, Re= 0.0000 meg for Boeing Mid (high subsonic).afl.
	tip  hi Re: alphamax=  16.00 deg, trat= 0.1000, Re=99.9000 meg for Boeing Mid (high subsonic).afl.
	Element # 1: S=   7.961 sqr mtrs, MAC=   8.66 mtrs, incidence=   2.80 deg.
	Element # 2: S=   7.695 sqr mtrs, MAC=   8.38 mtrs, incidence=   2.50 deg.
	Element # 3: S=   7.429 sqr mtrs, MAC=   8.09 mtrs, incidence=   2.20 deg.
	Element # 4: S=   7.163 sqr mtrs, MAC=   7.80 mtrs, incidence=   1.80 deg.
	Element # 5: S=   6.896 sqr mtrs, MAC=   7.51 mtrs, incidence=   1.50 deg.
	Element # 6: S=   6.630 sqr mtrs, MAC=   7.22 mtrs, incidence=   1.30 deg.
	Element # 7: S=   6.364 sqr mtrs, MAC=   6.93 mtrs, incidence=   1.10 deg.
	Element # 8: S=   6.098 sqr mtrs, MAC=   6.64 mtrs, incidence=   1.00 deg.
	Element # 9: S=   5.832 sqr mtrs, MAC=   6.35 mtrs, incidence=   0.90 deg.
	Element #10: S=   5.566 sqr mtrs, MAC=   6.06 mtrs, incidence=   0.80 deg.
	NOTE! I AM JOINING LEFT WING 3  TO LEFT WING 2  (through any intermediate wings) TO FORM ONE CONTINUOUS WING!
	NOTE! I AM JOINING LEFT WING 3  TO LEFT WING 4  (through any intermediate wings) TO FORM ONE CONTINUOUS WING!
	NOTE! I AM JOINING LEFT WING 3  TO MISC WING 7  (through any intermediate wings) TO FORM ONE CONTINUOUS WING!
	NOTE! I AM JOINING LEFT WING 3  TO LEFT WING 1  (through any intermediate wings) TO FORM ONE CONTINUOUS WING!
	After any wing-joining, our semi-length        is    40.75 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our root chord         is    16.49 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our tip chord          is     1.28 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our leading-edge sweep is    43.92 deg.  (for purposes of                        Delta-Wing factor determination only)
	After any wing-joining, our mean aero	 sweep is    40.07 deg.  (for purposes of Oswalds Efficiency                       determination only)
	After any wing-joining, our aspect ratio       is     7.05.      (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our taper ratio        is     0.08.      (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our washout            is     3.00 deg.  (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root=    3.00 deg, tip=    0.00 deg)
	Oswalds efficiency is therefore  0.9502, for lift-slope reduction to 78.61% of the 2-D value.
	We will accomplish this by:
		using coefficient data at an angle of attack that is 84.99% of actual (stall alpha=  18.83 deg),
		and reducing airfoil lift coefficients to            92.49% of their 2-D value.
		Based on AR and sweep, cm change is to               48.12% of the 2-D value.
		Based on AR and TR, aerodynamic center is moved      19.34% of the way from the the 25% chord to the 50% chord.

Finite-Wing & Element Build-Up for RIGT WING 3 :
	root lo Re: alphamax=  16.00 deg, trat= 0.1000, Re= 0.0000 meg for Boeing Mid (high subsonic).afl.
	root hi Re: alphamax=  16.00 deg, trat= 0.1000, Re=99.9000 meg for Boeing Mid (high subsonic).afl.
	tip  lo Re: alphamax=  16.00 deg, trat= 0.1000, Re= 0.0000 meg for Boeing Mid (high subsonic).afl.
	tip  hi Re: alphamax=  16.00 deg, trat= 0.1000, Re=99.9000 meg for Boeing Mid (high subsonic).afl.
	Element # 1: S=   7.961 sqr mtrs, MAC=   8.66 mtrs, incidence=   2.80 deg.
	Element # 2: S=   7.695 sqr mtrs, MAC=   8.38 mtrs, incidence=   2.50 deg.
	Element # 3: S=   7.429 sqr mtrs, MAC=   8.09 mtrs, incidence=   2.20 deg.
	Element # 4: S=   7.163 sqr mtrs, MAC=   7.80 mtrs, incidence=   1.80 deg.
	Element # 5: S=   6.896 sqr mtrs, MAC=   7.51 mtrs, incidence=   1.50 deg.
	Element # 6: S=   6.630 sqr mtrs, MAC=   7.22 mtrs, incidence=   1.30 deg.
	Element # 7: S=   6.364 sqr mtrs, MAC=   6.93 mtrs, incidence=   1.10 deg.
	Element # 8: S=   6.098 sqr mtrs, MAC=   6.64 mtrs, incidence=   1.00 deg.
	Element # 9: S=   5.832 sqr mtrs, MAC=   6.35 mtrs, incidence=   0.90 deg.
	Element #10: S=   5.566 sqr mtrs, MAC=   6.06 mtrs, incidence=   0.80 deg.
	NOTE! I AM JOINING RIGT WING 3  TO RIGT WING 2  (through any intermediate wings) TO FORM ONE CONTINUOUS WING!
	NOTE! I AM JOINING RIGT WING 3  TO RIGT WING 4  (through any intermediate wings) TO FORM ONE CONTINUOUS WING!
	NOTE! I AM JOINING RIGT WING 3  TO MISC WING 8  (through any intermediate wings) TO FORM ONE CONTINUOUS WING!
	NOTE! I AM JOINING RIGT WING 3  TO RIGT WING 1  (through any intermediate wings) TO FORM ONE CONTINUOUS WING!
	After any wing-joining, our semi-length        is    40.75 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our root chord         is    16.49 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our tip chord          is     1.28 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our leading-edge sweep is    43.92 deg.  (for purposes of                        Delta-Wing factor determination only)
	After any wing-joining, our mean aero	 sweep is    40.06 deg.  (for purposes of Oswalds Efficiency                       determination only)
	After any wing-joining, our aspect ratio       is     7.05.      (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our taper ratio        is     0.08.      (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our washout            is     3.00 deg.  (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root=    3.00 deg, tip=    0.00 deg)
	Oswalds efficiency is therefore  0.9502, for lift-slope reduction to 78.61% of the 2-D value.
	We will accomplish this by:
		using coefficient data at an angle of attack that is 84.99% of actual (stall alpha=  18.83 deg),
		and reducing airfoil lift coefficients to            92.49% of their 2-D value.
		Based on AR and sweep, cm change is to               48.13% of the 2-D value.
		Based on AR and TR, aerodynamic center is moved      19.33% of the way from the the 25% chord to the 50% chord.

Finite-Wing & Element Build-Up for LEFT WING 4 :
	root lo Re: alphamax=  16.00 deg, trat= 0.1000, Re= 0.0000 meg for Boeing Mid (high subsonic).afl.
	root hi Re: alphamax=  16.00 deg, trat= 0.1000, Re=99.9000 meg for Boeing Mid (high subsonic).afl.
	tip  lo Re: alphamax=  16.00 deg, trat= 0.0850, Re= 0.0000 meg for Boeing Tip (high subsonic).afl.
	tip  hi Re: alphamax=  16.00 deg, trat= 0.0850, Re=99.9000 meg for Boeing Tip (high subsonic).afl.
	Element # 1: S=   4.486 sqr mtrs, MAC=   5.82 mtrs, incidence=   0.80 deg.
	Element # 2: S=   4.345 sqr mtrs, MAC=   5.64 mtrs, incidence=   0.70 deg.
	Element # 3: S=   4.205 sqr mtrs, MAC=   5.46 mtrs, incidence=   0.50 deg.
	Element # 4: S=   4.064 sqr mtrs, MAC=   5.27 mtrs, incidence=   0.40 deg.
	Element # 5: S=   3.923 sqr mtrs, MAC=   5.09 mtrs, incidence=   0.30 deg.
	Element # 6: S=   3.782 sqr mtrs, MAC=   4.91 mtrs, incidence=   0.20 deg.
	Element # 7: S=   3.641 sqr mtrs, MAC=   4.72 mtrs, incidence=   0.10 deg.
	Element # 8: S=   3.500 sqr mtrs, MAC=   4.54 mtrs, incidence=   0.00 deg.
	Element # 9: S=   3.359 sqr mtrs, MAC=   4.36 mtrs, incidence=   0.00 deg.
	Element #10: S=   3.218 sqr mtrs, MAC=   4.18 mtrs, incidence=   0.00 deg.
	NOTE! I AM JOINING LEFT WING 4  TO LEFT WING 3  (through any intermediate wings) TO FORM ONE CONTINUOUS WING!
	NOTE! I AM JOINING LEFT WING 4  TO MISC WING 7  (through any intermediate wings) TO FORM ONE CONTINUOUS WING!
	NOTE! I AM JOINING LEFT WING 4  TO LEFT WING 2  (through any intermediate wings) TO FORM ONE CONTINUOUS WING!
	NOTE! I AM JOINING LEFT WING 4  TO LEFT WING 1  (through any intermediate wings) TO FORM ONE CONTINUOUS WING!
	After any wing-joining, our semi-length        is    40.75 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our root chord         is    16.49 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our tip chord          is     1.28 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our leading-edge sweep is    43.92 deg.  (for purposes of                        Delta-Wing factor determination only)
	After any wing-joining, our mean aero	 sweep is    40.07 deg.  (for purposes of Oswalds Efficiency                       determination only)
	After any wing-joining, our aspect ratio       is     7.05.      (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our taper ratio        is     0.08.      (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our washout            is     3.00 deg.  (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root=    3.00 deg, tip=    0.00 deg)
	Oswalds efficiency is therefore  0.9502, for lift-slope reduction to 78.61% of the 2-D value.
	We will accomplish this by:
		using coefficient data at an angle of attack that is 84.99% of actual (stall alpha=  18.83 deg),
		and reducing airfoil lift coefficients to            92.49% of their 2-D value.
		Based on AR and sweep, cm change is to               48.12% of the 2-D value.
		Based on AR and TR, aerodynamic center is moved      19.34% of the way from the the 25% chord to the 50% chord.

Finite-Wing & Element Build-Up for RIGT WING 4 :
	root lo Re: alphamax=  16.00 deg, trat= 0.1000, Re= 0.0000 meg for Boeing Mid (high subsonic).afl.
	root hi Re: alphamax=  16.00 deg, trat= 0.1000, Re=99.9000 meg for Boeing Mid (high subsonic).afl.
	tip  lo Re: alphamax=  16.00 deg, trat= 0.0850, Re= 0.0000 meg for Boeing Tip (high subsonic).afl.
	tip  hi Re: alphamax=  16.00 deg, trat= 0.0850, Re=99.9000 meg for Boeing Tip (high subsonic).afl.
	Element # 1: S=   4.486 sqr mtrs, MAC=   5.82 mtrs, incidence=   0.80 deg.
	Element # 2: S=   4.345 sqr mtrs, MAC=   5.64 mtrs, incidence=   0.70 deg.
	Element # 3: S=   4.205 sqr mtrs, MAC=   5.46 mtrs, incidence=   0.50 deg.
	Element # 4: S=   4.064 sqr mtrs, MAC=   5.27 mtrs, incidence=   0.40 deg.
	Element # 5: S=   3.923 sqr mtrs, MAC=   5.09 mtrs, incidence=   0.30 deg.
	Element # 6: S=   3.782 sqr mtrs, MAC=   4.91 mtrs, incidence=   0.20 deg.
	Element # 7: S=   3.641 sqr mtrs, MAC=   4.72 mtrs, incidence=   0.10 deg.
	Element # 8: S=   3.500 sqr mtrs, MAC=   4.54 mtrs, incidence=   0.00 deg.
	Element # 9: S=   3.359 sqr mtrs, MAC=   4.36 mtrs, incidence=   0.00 deg.
	Element #10: S=   3.218 sqr mtrs, MAC=   4.18 mtrs, incidence=   0.00 deg.
	NOTE! I AM JOINING RIGT WING 4  TO RIGT WING 3  (through any intermediate wings) TO FORM ONE CONTINUOUS WING!
	NOTE! I AM JOINING RIGT WING 4  TO MISC WING 8  (through any intermediate wings) TO FORM ONE CONTINUOUS WING!
	NOTE! I AM JOINING RIGT WING 4  TO RIGT WING 2  (through any intermediate wings) TO FORM ONE CONTINUOUS WING!
	NOTE! I AM JOINING RIGT WING 4  TO RIGT WING 1  (through any intermediate wings) TO FORM ONE CONTINUOUS WING!
	After any wing-joining, our semi-length        is    40.75 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our root chord         is    16.49 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our tip chord          is     1.28 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our leading-edge sweep is    43.92 deg.  (for purposes of                        Delta-Wing factor determination only)
	After any wing-joining, our mean aero	 sweep is    40.06 deg.  (for purposes of Oswalds Efficiency                       determination only)
	After any wing-joining, our aspect ratio       is     7.05.      (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our taper ratio        is     0.08.      (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our washout            is     3.00 deg.  (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root=    3.00 deg, tip=    0.00 deg)
	Oswalds efficiency is therefore  0.9502, for lift-slope reduction to 78.61% of the 2-D value.
	We will accomplish this by:
		using coefficient data at an angle of attack that is 84.99% of actual (stall alpha=  18.83 deg),
		and reducing airfoil lift coefficients to            92.49% of their 2-D value.
		Based on AR and sweep, cm change is to               48.13% of the 2-D value.
		Based on AR and TR, aerodynamic center is moved      19.33% of the way from the the 25% chord to the 50% chord.

Finite-Wing & Element Build-Up for LEFT H-STAB :
	root lo Re: alphamax=  15.00 deg, trat= 0.1200, Re= 0.0000 meg for NACA 2412 (popular) invert.afl.
	root hi Re: alphamax=  15.00 deg, trat= 0.1200, Re=99.9000 meg for NACA 2412 (popular) invert.afl.
	tip  lo Re: alphamax=  15.00 deg, trat= 0.1200, Re= 0.0000 meg for NACA 2412 (popular) invert.afl.
	tip  hi Re: alphamax=  15.00 deg, trat= 0.1200, Re=99.9000 meg for NACA 2412 (popular) invert.afl.
	Element # 1: S=  14.721 sqr mtrs, MAC=   9.30 mtrs, incidence=   0.00 deg.
	Element # 2: S=  13.066 sqr mtrs, MAC=   8.26 mtrs, incidence=   0.00 deg.
	Element # 3: S=  11.410 sqr mtrs, MAC=   7.21 mtrs, incidence=   0.00 deg.
	Element # 4: S=   9.754 sqr mtrs, MAC=   6.17 mtrs, incidence=   0.00 deg.
	Element # 5: S=   8.099 sqr mtrs, MAC=   5.13 mtrs, incidence=   0.00 deg.
	Element # 6: S=   6.443 sqr mtrs, MAC=   4.09 mtrs, incidence=   0.00 deg.
	Element # 7: S=   4.787 sqr mtrs, MAC=   3.05 mtrs, incidence=   0.00 deg.
	After any wing-joining, our semi-length        is    13.96 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our root chord         is     9.81 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our tip chord          is     2.50 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our leading-edge sweep is    42.91 deg.  (for purposes of                        Delta-Wing factor determination only)
	After any wing-joining, our mean aero	 sweep is    37.40 deg.  (for purposes of Oswalds Efficiency                       determination only)
	After any wing-joining, our aspect ratio       is     3.60.      (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our taper ratio        is     0.25.      (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our washout            is     0.00 deg.  (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root=    0.00 deg, tip=    0.00 deg)
	Oswalds efficiency is therefore  0.9896, for lift-slope reduction to 66.16% of the 2-D value.
	We will accomplish this by:
		using coefficient data at an angle of attack that is 75.42% of actual (stall alpha=  19.89 deg),
		and reducing airfoil lift coefficients to            87.71% of their 2-D value.
		Based on AR and sweep, cm change is to               43.79% of the 2-D value.
		Based on AR and TR, aerodynamic center is moved      33.13% of the way from the the 25% chord to the 50% chord.

Finite-Wing & Element Build-Up for RIGT H-STAB :
	root lo Re: alphamax=  15.00 deg, trat= 0.1200, Re= 0.0000 meg for NACA 2412 (popular) invert.afl.
	root hi Re: alphamax=  15.00 deg, trat= 0.1200, Re=99.9000 meg for NACA 2412 (popular) invert.afl.
	tip  lo Re: alphamax=  15.00 deg, trat= 0.1200, Re= 0.0000 meg for NACA 2412 (popular) invert.afl.
	tip  hi Re: alphamax=  15.00 deg, trat= 0.1200, Re=99.9000 meg for NACA 2412 (popular) invert.afl.
	Element # 1: S=  14.721 sqr mtrs, MAC=   9.30 mtrs, incidence=   0.00 deg.
	Element # 2: S=  13.066 sqr mtrs, MAC=   8.26 mtrs, incidence=   0.00 deg.
	Element # 3: S=  11.410 sqr mtrs, MAC=   7.21 mtrs, incidence=   0.00 deg.
	Element # 4: S=   9.754 sqr mtrs, MAC=   6.17 mtrs, incidence=   0.00 deg.
	Element # 5: S=   8.099 sqr mtrs, MAC=   5.13 mtrs, incidence=   0.00 deg.
	Element # 6: S=   6.443 sqr mtrs, MAC=   4.09 mtrs, incidence=   0.00 deg.
	Element # 7: S=   4.787 sqr mtrs, MAC=   3.05 mtrs, incidence=   0.00 deg.
	After any wing-joining, our semi-length        is    13.96 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our root chord         is     9.81 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our tip chord          is     2.50 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our leading-edge sweep is    42.91 deg.  (for purposes of                        Delta-Wing factor determination only)
	After any wing-joining, our mean aero	 sweep is    37.40 deg.  (for purposes of Oswalds Efficiency                       determination only)
	After any wing-joining, our aspect ratio       is     3.60.      (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our taper ratio        is     0.25.      (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our washout            is     0.00 deg.  (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root=    0.00 deg, tip=    0.00 deg)
	Oswalds efficiency is therefore  0.9896, for lift-slope reduction to 66.16% of the 2-D value.
	We will accomplish this by:
		using coefficient data at an angle of attack that is 75.42% of actual (stall alpha=  19.89 deg),
		and reducing airfoil lift coefficients to            87.71% of their 2-D value.
		Based on AR and sweep, cm change is to               43.79% of the 2-D value.
		Based on AR and TR, aerodynamic center is moved      33.13% of the way from the the 25% chord to the 50% chord.

Finite-Wing & Element Build-Up for VERT STAB 1 :
	root lo Re: alphamax=  13.50 deg, trat= 0.0900, Re= 0.0000 meg for NACA 0009 (symmetrical).afl.
	root hi Re: alphamax=  13.50 deg, trat= 0.0900, Re=99.9000 meg for NACA 0009 (symmetrical).afl.
	tip  lo Re: alphamax=  13.50 deg, trat= 0.0900, Re= 0.0000 meg for NACA 0009 (symmetrical).afl.
	tip  hi Re: alphamax=  13.50 deg, trat= 0.0900, Re=99.9000 meg for NACA 0009 (symmetrical).afl.
	Element # 1: S=   2.477 sqr mtrs, MAC=   9.13 mtrs, incidence=   0.00 deg.
	Element # 2: S=   2.317 sqr mtrs, MAC=   8.54 mtrs, incidence=   0.00 deg.
	Element # 3: S=   2.158 sqr mtrs, MAC=   7.96 mtrs, incidence=   0.00 deg.
	Element # 4: S=   1.999 sqr mtrs, MAC=   7.37 mtrs, incidence=   0.00 deg.
	After any wing-joining, our semi-length        is     2.41 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our root chord         is     9.42 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our tip chord          is     7.07 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our leading-edge sweep is    68.36 deg.  (for purposes of                        Delta-Wing factor determination only)
	After any wing-joining, our mean aero	 sweep is    63.20 deg.  (for purposes of Oswalds Efficiency                       determination only)
	After any wing-joining, our aspect ratio       is     0.50.      (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our taper ratio        is     0.75.      (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our washout            is     0.00 deg.  (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root=    0.00 deg, tip=    0.00 deg)
	Oswalds efficiency is therefore  0.9773, for lift-slope reduction to 21.13% of the 2-D value.
	We will accomplish this by:
		using coefficient data at an angle of attack that is 32.01% of actual (stall alpha=  42.17 deg),
		and reducing airfoil lift coefficients to            66.01% of their 2-D value.
		Based on AR and sweep, cm change is to               7.25% of the 2-D value.
		Based on AR and TR, aerodynamic center is moved      24.92% of the way from the the 25% chord to the 50% chord.

Finite-Wing & Element Build-Up for VERT STAB 2 :
	root lo Re: alphamax=  13.50 deg, trat= 0.1200, Re= 0.0000 meg for NACA 0012 (symmetrical).afl.
	root hi Re: alphamax=  13.50 deg, trat= 0.1200, Re=99.9000 meg for NACA 0012 (symmetrical).afl.
	tip  lo Re: alphamax=  13.50 deg, trat= 0.0900, Re= 0.0000 meg for NACA 0009 (symmetrical).afl.
	tip  hi Re: alphamax=  13.50 deg, trat= 0.0900, Re=99.9000 meg for NACA 0009 (symmetrical).afl.
	Element # 1: S=  11.757 sqr mtrs, MAC=  11.59 mtrs, incidence=   0.00 deg.
	Element # 2: S=  10.949 sqr mtrs, MAC=  10.79 mtrs, incidence=   0.00 deg.
	Element # 3: S=  10.141 sqr mtrs, MAC=  10.00 mtrs, incidence=   0.00 deg.
	Element # 4: S=   9.334 sqr mtrs, MAC=   9.20 mtrs, incidence=   0.00 deg.
	Element # 5: S=   8.526 sqr mtrs, MAC=   8.41 mtrs, incidence=   0.00 deg.
	Element # 6: S=   7.719 sqr mtrs, MAC=   7.61 mtrs, incidence=   0.00 deg.
	Element # 7: S=   6.911 sqr mtrs, MAC=   6.82 mtrs, incidence=   0.00 deg.
	Element # 8: S=   6.103 sqr mtrs, MAC=   6.02 mtrs, incidence=   0.00 deg.
	Element # 9: S=   5.296 sqr mtrs, MAC=   5.23 mtrs, incidence=   0.00 deg.
	Element #10: S=   4.488 sqr mtrs, MAC=   4.43 mtrs, incidence=   0.00 deg.
	After any wing-joining, our semi-length        is    14.33 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our root chord         is    11.98 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our tip chord          is     4.02 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our leading-edge sweep is    50.02 deg.  (for purposes of                        Delta-Wing factor determination only)
	After any wing-joining, our mean aero	 sweep is    44.90 deg.  (for purposes of Oswalds Efficiency                       determination only)
	After any wing-joining, our aspect ratio       is     2.54.      (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our taper ratio        is     0.34.      (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our washout            is     0.00 deg.  (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root=    0.00 deg, tip=    0.00 deg)
	Oswalds efficiency is therefore  0.9826, for lift-slope reduction to 57.76% of the 2-D value.
	We will accomplish this by:
		using coefficient data at an angle of attack that is 68.54% of actual (stall alpha=  19.70 deg),
		and reducing airfoil lift coefficients to            84.27% of their 2-D value.
		Based on AR and sweep, cm change is to               32.20% of the 2-D value.
		Based on AR and TR, aerodynamic center is moved      40.14% of the way from the the 25% chord to the 50% chord.

Finite-Wing & Element Build-Up for MISC WING 1 :
	root lo Re: alphamax=  13.50 deg, trat= 0.0900, Re= 0.0000 meg for NACA 0009 (symmetrical).afl.
	root hi Re: alphamax=  13.50 deg, trat= 0.0900, Re=99.9000 meg for NACA 0009 (symmetrical).afl.
	tip  lo Re: alphamax=  13.50 deg, trat= 0.0900, Re= 0.0000 meg for NACA 0009 (symmetrical).afl.
	tip  hi Re: alphamax=  13.50 deg, trat= 0.0900, Re=99.9000 meg for NACA 0009 (symmetrical).afl.
	Element # 1: S=   0.060 sqr mtrs, MAC=   0.24 mtrs, incidence=   0.00 deg.
	Element # 2: S=   0.040 sqr mtrs, MAC=   0.16 mtrs, incidence=   0.00 deg.
	After any wing-joining, our semi-length        is     0.61 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our root chord         is     0.27 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our tip chord          is     0.12 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our leading-edge sweep is    36.87 deg.  (for purposes of                        Delta-Wing factor determination only)
	After any wing-joining, our mean aero	 sweep is    34.00 deg.  (for purposes of Oswalds Efficiency                       determination only)
	After any wing-joining, our aspect ratio       is     5.10.      (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our taper ratio        is     0.44.      (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our washout            is     0.00 deg.  (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root=    0.00 deg, tip=    0.00 deg)
	Oswalds efficiency is therefore  0.9841, for lift-slope reduction to 73.35% of the 2-D value.
	We will accomplish this by:
		using coefficient data at an angle of attack that is 81.04% of actual (stall alpha=  16.66 deg),
		and reducing airfoil lift coefficients to            90.52% of their 2-D value.
		Based on AR and sweep, cm change is to               51.87% of the 2-D value.
		Based on AR and TR, aerodynamic center is moved      16.25% of the way from the the 25% chord to the 50% chord.

Finite-Wing & Element Build-Up for MISC WING 2 :
	root lo Re: alphamax=  13.50 deg, trat= 0.0900, Re= 0.0000 meg for NACA 0009 (symmetrical).afl.
	root hi Re: alphamax=  13.50 deg, trat= 0.0900, Re=99.9000 meg for NACA 0009 (symmetrical).afl.
	tip  lo Re: alphamax=  13.50 deg, trat= 0.0900, Re= 0.0000 meg for NACA 0009 (symmetrical).afl.
	tip  hi Re: alphamax=  13.50 deg, trat= 0.0900, Re=99.9000 meg for NACA 0009 (symmetrical).afl.
	Element # 1: S=   0.057 sqr mtrs, MAC=   0.24 mtrs, incidence=   0.00 deg.
	Element # 2: S=   0.038 sqr mtrs, MAC=   0.16 mtrs, incidence=   0.00 deg.
	After any wing-joining, our semi-length        is     0.58 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our root chord         is     0.27 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our tip chord          is     0.12 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our leading-edge sweep is    37.01 deg.  (for purposes of                        Delta-Wing factor determination only)
	After any wing-joining, our mean aero	 sweep is    34.00 deg.  (for purposes of Oswalds Efficiency                       determination only)
	After any wing-joining, our aspect ratio       is     4.85.      (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our taper ratio        is     0.44.      (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our washout            is     0.00 deg.  (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root=    0.00 deg, tip=    0.00 deg)
	Oswalds efficiency is therefore  0.9843, for lift-slope reduction to 72.34% of the 2-D value.
	We will accomplish this by:
		using coefficient data at an angle of attack that is 80.26% of actual (stall alpha=  16.82 deg),
		and reducing airfoil lift coefficients to            90.13% of their 2-D value.
		Based on AR and sweep, cm change is to               51.21% of the 2-D value.
		Based on AR and TR, aerodynamic center is moved      17.16% of the way from the the 25% chord to the 50% chord.

Finite-Wing & Element Build-Up for MISC WING 3 :
	root lo Re: alphamax=  13.50 deg, trat= 0.0900, Re= 0.0000 meg for NACA 0009 (symmetrical).afl.
	root hi Re: alphamax=  13.50 deg, trat= 0.0900, Re=99.9000 meg for NACA 0009 (symmetrical).afl.
	tip  lo Re: alphamax=  13.50 deg, trat= 0.0900, Re= 0.0000 meg for NACA 0009 (symmetrical).afl.
	tip  hi Re: alphamax=  13.50 deg, trat= 0.0900, Re=99.9000 meg for NACA 0009 (symmetrical).afl.
	Element # 1: S=   0.027 sqr mtrs, MAC=   0.28 mtrs, incidence=   0.00 deg.
	Element # 2: S=   0.021 sqr mtrs, MAC=   0.21 mtrs, incidence=   0.00 deg.
	After any wing-joining, our semi-length        is     0.30 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our root chord         is     0.30 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our tip chord          is     0.18 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our leading-edge sweep is    53.42 deg.  (for purposes of                        Delta-Wing factor determination only)
	After any wing-joining, our mean aero	 sweep is    50.00 deg.  (for purposes of Oswalds Efficiency                       determination only)
	After any wing-joining, our aspect ratio       is     1.61.      (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our taper ratio        is     0.60.      (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our washout            is     0.00 deg.  (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root=    0.00 deg, tip=    0.00 deg)
	Oswalds efficiency is therefore  0.9748, for lift-slope reduction to 46.21% of the 2-D value.
	We will accomplish this by:
		using coefficient data at an angle of attack that is 58.36% of actual (stall alpha=  23.13 deg),
		and reducing airfoil lift coefficients to            79.18% of their 2-D value.
		Based on AR and sweep, cm change is to               22.95% of the 2-D value.
		Based on AR and TR, aerodynamic center is moved      29.04% of the way from the the 25% chord to the 50% chord.

Finite-Wing & Element Build-Up for MISC WING 5 :
	root lo Re: alphamax=  13.50 deg, trat= 0.0900, Re= 0.0000 meg for NACA 0009 (symmetrical).afl.
	root hi Re: alphamax=  13.50 deg, trat= 0.0900, Re=99.9000 meg for NACA 0009 (symmetrical).afl.
	tip  lo Re: alphamax=  13.50 deg, trat= 0.0900, Re= 0.0000 meg for NACA 0009 (symmetrical).afl.
	tip  hi Re: alphamax=  13.50 deg, trat= 0.0900, Re=99.9000 meg for NACA 0009 (symmetrical).afl.
	Element # 1: S=   0.045 sqr mtrs, MAC=   0.28 mtrs, incidence=   0.00 deg.
	Element # 2: S=   0.035 sqr mtrs, MAC=   0.21 mtrs, incidence=   0.00 deg.
	After any wing-joining, our semi-length        is     0.49 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our root chord         is     0.30 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our tip chord          is     0.18 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our leading-edge sweep is    50.29 deg.  (for purposes of                        Delta-Wing factor determination only)
	After any wing-joining, our mean aero	 sweep is    48.00 deg.  (for purposes of Oswalds Efficiency                       determination only)
	After any wing-joining, our aspect ratio       is     2.68.      (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our taper ratio        is     0.60.      (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our washout            is     0.00 deg.  (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root=    0.00 deg, tip=    0.00 deg)
	Oswalds efficiency is therefore  0.9658, for lift-slope reduction to 58.63% of the 2-D value.
	We will accomplish this by:
		using coefficient data at an angle of attack that is 69.28% of actual (stall alpha=  19.49 deg),
		and reducing airfoil lift coefficients to            84.64% of their 2-D value.
		Based on AR and sweep, cm change is to               29.85% of the 2-D value.
		Based on AR and TR, aerodynamic center is moved      23.86% of the way from the the 25% chord to the 50% chord.

Finite-Wing & Element Build-Up for MISC WING 6 :
	root lo Re: alphamax=  13.50 deg, trat= 0.0900, Re= 0.0000 meg for NACA 0009 (symmetrical).afl.
	root hi Re: alphamax=  13.50 deg, trat= 0.0900, Re=99.9000 meg for NACA 0009 (symmetrical).afl.
	tip  lo Re: alphamax=  13.50 deg, trat= 0.0900, Re= 0.0000 meg for NACA 0009 (symmetrical).afl.
	tip  hi Re: alphamax=  13.50 deg, trat= 0.0900, Re=99.9000 meg for NACA 0009 (symmetrical).afl.
	Element # 1: S=   0.032 sqr mtrs, MAC=   0.28 mtrs, incidence=   0.00 deg.
	Element # 2: S=   0.025 sqr mtrs, MAC=   0.21 mtrs, incidence=   0.00 deg.
	After any wing-joining, our semi-length        is     0.37 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our root chord         is     0.30 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our tip chord          is     0.18 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our leading-edge sweep is    52.88 deg.  (for purposes of                        Delta-Wing factor determination only)
	After any wing-joining, our mean aero	 sweep is    50.00 deg.  (for purposes of Oswalds Efficiency                       determination only)
	After any wing-joining, our aspect ratio       is     1.93.      (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our taper ratio        is     0.60.      (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our washout            is     0.00 deg.  (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root=    0.00 deg, tip=    0.00 deg)
	Oswalds efficiency is therefore  0.9713, for lift-slope reduction to 50.67% of the 2-D value.
	We will accomplish this by:
		using coefficient data at an angle of attack that is 62.40% of actual (stall alpha=  21.64 deg),
		and reducing airfoil lift coefficients to            81.20% of their 2-D value.
		Based on AR and sweep, cm change is to               24.79% of the 2-D value.
		Based on AR and TR, aerodynamic center is moved      27.65% of the way from the the 25% chord to the 50% chord.

Finite-Wing & Element Build-Up for MISC WING 7 :
	root lo Re: alphamax=  13.50 deg, trat= 0.0900, Re= 0.0000 meg for NACA 0009 (symmetrical).afl.
	root hi Re: alphamax=  13.50 deg, trat= 0.0900, Re=99.9000 meg for NACA 0009 (symmetrical).afl.
	tip  lo Re: alphamax=  13.50 deg, trat= 0.0900, Re= 0.0000 meg for NACA 0009 (symmetrical).afl.
	tip  hi Re: alphamax=  13.50 deg, trat= 0.0900, Re=99.9000 meg for NACA 0009 (symmetrical).afl.
	Element # 1: S=   2.494 sqr mtrs, MAC=   2.58 mtrs, incidence=   0.00 deg.
	Element # 2: S=   1.663 sqr mtrs, MAC=   1.74 mtrs, incidence=   0.00 deg.
	NOTE! I AM JOINING MISC WING 7  TO LEFT WING 4  (through any intermediate wings) TO FORM ONE CONTINUOUS WING!
	NOTE! I AM JOINING MISC WING 7  TO LEFT WING 3  (through any intermediate wings) TO FORM ONE CONTINUOUS WING!
	NOTE! I AM JOINING MISC WING 7  TO LEFT WING 2  (through any intermediate wings) TO FORM ONE CONTINUOUS WING!
	NOTE! I AM JOINING MISC WING 7  TO LEFT WING 1  (through any intermediate wings) TO FORM ONE CONTINUOUS WING!
	After any wing-joining, our semi-length        is    40.75 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our root chord         is    16.49 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our tip chord          is     1.28 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our leading-edge sweep is    43.92 deg.  (for purposes of                        Delta-Wing factor determination only)
	After any wing-joining, our mean aero	 sweep is    40.07 deg.  (for purposes of Oswalds Efficiency                       determination only)
	After any wing-joining, our aspect ratio       is     7.05.      (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our taper ratio        is     0.08.      (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our washout            is     3.00 deg.  (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root=    3.00 deg, tip=    0.00 deg)
	Oswalds efficiency is therefore  0.9502, for lift-slope reduction to 78.61% of the 2-D value.
	We will accomplish this by:
		using coefficient data at an angle of attack that is 84.99% of actual (stall alpha=  15.89 deg),
		and reducing airfoil lift coefficients to            92.49% of their 2-D value.
		Based on AR and sweep, cm change is to               48.12% of the 2-D value.
		Based on AR and TR, aerodynamic center is moved      19.34% of the way from the the 25% chord to the 50% chord.

Finite-Wing & Element Build-Up for MISC WING 8 :
	root lo Re: alphamax=  13.50 deg, trat= 0.0900, Re= 0.0000 meg for NACA 0009 (symmetrical).afl.
	root hi Re: alphamax=  13.50 deg, trat= 0.0900, Re=99.9000 meg for NACA 0009 (symmetrical).afl.
	tip  lo Re: alphamax=  13.50 deg, trat= 0.0900, Re= 0.0000 meg for NACA 0009 (symmetrical).afl.
	tip  hi Re: alphamax=  13.50 deg, trat= 0.0900, Re=99.9000 meg for NACA 0009 (symmetrical).afl.
	Element # 1: S=   2.494 sqr mtrs, MAC=   2.58 mtrs, incidence=   0.00 deg.
	Element # 2: S=   1.663 sqr mtrs, MAC=   1.74 mtrs, incidence=   0.00 deg.
	NOTE! I AM JOINING MISC WING 8  TO RIGT WING 4  (through any intermediate wings) TO FORM ONE CONTINUOUS WING!
	NOTE! I AM JOINING MISC WING 8  TO RIGT WING 3  (through any intermediate wings) TO FORM ONE CONTINUOUS WING!
	NOTE! I AM JOINING MISC WING 8  TO RIGT WING 2  (through any intermediate wings) TO FORM ONE CONTINUOUS WING!
	NOTE! I AM JOINING MISC WING 8  TO RIGT WING 1  (through any intermediate wings) TO FORM ONE CONTINUOUS WING!
	After any wing-joining, our semi-length        is    40.75 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our root chord         is    16.49 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our tip chord          is     1.28 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our leading-edge sweep is    43.92 deg.  (for purposes of                        Delta-Wing factor determination only)
	After any wing-joining, our mean aero	 sweep is    40.06 deg.  (for purposes of Oswalds Efficiency                       determination only)
	After any wing-joining, our aspect ratio       is     7.05.      (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our taper ratio        is     0.08.      (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our washout            is     3.00 deg.  (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root=    3.00 deg, tip=    0.00 deg)
	Oswalds efficiency is therefore  0.9502, for lift-slope reduction to 78.61% of the 2-D value.
	We will accomplish this by:
		using coefficient data at an angle of attack that is 84.99% of actual (stall alpha=  15.88 deg),
		and reducing airfoil lift coefficients to            92.49% of their 2-D value.
		Based on AR and sweep, cm change is to               48.13% of the 2-D value.
		Based on AR and TR, aerodynamic center is moved      19.33% of the way from the the 25% chord to the 50% chord.

Finite-Wing & Element Build-Up for ENG PYLN 1a :
	root lo Re: alphamax=  13.50 deg, trat= 0.0900, Re= 0.0000 meg for NACA 0009 (symmetrical).afl.
	root hi Re: alphamax=  13.50 deg, trat= 0.0900, Re=99.9000 meg for NACA 0009 (symmetrical).afl.
	tip  lo Re: alphamax=  13.50 deg, trat= 0.0900, Re= 0.0000 meg for NACA 0009 (symmetrical).afl.
	tip  hi Re: alphamax=  13.50 deg, trat= 0.0900, Re=99.9000 meg for NACA 0009 (symmetrical).afl.
	Element # 1: S=   7.302 sqr mtrs, MAC=   6.70 mtrs, incidence=   0.00 deg.
	Applying biplane interference factor to Oswalds Efficiency! between ENG PYLN 1a  and ENG PYLN 2a 
	After any wing-joining, our semi-length        is     4.51 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our root chord         is     7.99 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our tip chord          is     5.21 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our leading-edge sweep is    77.68 deg.  (for purposes of                        Delta-Wing factor determination only)
	After any wing-joining, our mean aero	 sweep is    75.80 deg.  (for purposes of Oswalds Efficiency                       determination only)
	After any wing-joining, our aspect ratio       is     0.50.      (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our taper ratio        is     0.65.      (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our washout            is     0.00 deg.  (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root=    0.00 deg, tip=    0.00 deg)
	Oswalds efficiency is therefore  0.5000, for lift-slope reduction to 12.06% of the 2-D value.
	We will accomplish this by:
		using coefficient data at an angle of attack that is 20.08% of actual (stall alpha=  67.23 deg),
		and reducing airfoil lift coefficients to            60.04% of their 2-D value.
		Based on AR and sweep, cm change is to               3.04% of the 2-D value.
		Based on AR and TR, aerodynamic center is moved      34.73% of the way from the the 25% chord to the 50% chord.

Finite-Wing & Element Build-Up for ENG PYLN 2a :
	root lo Re: alphamax=  13.50 deg, trat= 0.0900, Re= 0.0000 meg for NACA 0009 (symmetrical).afl.
	root hi Re: alphamax=  13.50 deg, trat= 0.0900, Re=99.9000 meg for NACA 0009 (symmetrical).afl.
	tip  lo Re: alphamax=  13.50 deg, trat= 0.0900, Re= 0.0000 meg for NACA 0009 (symmetrical).afl.
	tip  hi Re: alphamax=  13.50 deg, trat= 0.0900, Re=99.9000 meg for NACA 0009 (symmetrical).afl.
	Element # 1: S=   7.302 sqr mtrs, MAC=   6.70 mtrs, incidence=   0.00 deg.
	Applying biplane interference factor to Oswalds Efficiency! between ENG PYLN 2a  and ENG PYLN 1a 
	After any wing-joining, our semi-length        is     4.51 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our root chord         is     7.99 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our tip chord          is     5.21 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our leading-edge sweep is    77.68 deg.  (for purposes of                        Delta-Wing factor determination only)
	After any wing-joining, our mean aero	 sweep is    75.80 deg.  (for purposes of Oswalds Efficiency                       determination only)
	After any wing-joining, our aspect ratio       is     0.50.      (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our taper ratio        is     0.65.      (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our washout            is     0.00 deg.  (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root=    0.00 deg, tip=    0.00 deg)
	Oswalds efficiency is therefore  0.5000, for lift-slope reduction to 12.06% of the 2-D value.
	We will accomplish this by:
		using coefficient data at an angle of attack that is 20.08% of actual (stall alpha=  67.23 deg),
		and reducing airfoil lift coefficients to            60.04% of their 2-D value.
		Based on AR and sweep, cm change is to               3.04% of the 2-D value.
		Based on AR and TR, aerodynamic center is moved      34.73% of the way from the the 25% chord to the 50% chord.

Finite-Wing & Element Build-Up for ENG PYLN 3a :
	root lo Re: alphamax=  13.50 deg, trat= 0.0900, Re= 0.0000 meg for NACA 0009 (symmetrical).afl.
	root hi Re: alphamax=  13.50 deg, trat= 0.0900, Re=99.9000 meg for NACA 0009 (symmetrical).afl.
	tip  lo Re: alphamax=  13.50 deg, trat= 0.0900, Re= 0.0000 meg for NACA 0009 (symmetrical).afl.
	tip  hi Re: alphamax=  13.50 deg, trat= 0.0900, Re=99.9000 meg for NACA 0009 (symmetrical).afl.
	Element # 1: S=   7.302 sqr mtrs, MAC=   6.70 mtrs, incidence=   0.00 deg.
	Applying biplane interference factor to Oswalds Efficiency! between ENG PYLN 3a  and ENG PYLN 4a 
	After any wing-joining, our semi-length        is     4.51 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our root chord         is     7.99 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our tip chord          is     5.21 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our leading-edge sweep is    77.68 deg.  (for purposes of                        Delta-Wing factor determination only)
	After any wing-joining, our mean aero	 sweep is    75.80 deg.  (for purposes of Oswalds Efficiency                       determination only)
	After any wing-joining, our aspect ratio       is     0.50.      (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our taper ratio        is     0.65.      (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our washout            is     0.00 deg.  (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root=    0.00 deg, tip=    0.00 deg)
	Oswalds efficiency is therefore  0.5000, for lift-slope reduction to 12.06% of the 2-D value.
	We will accomplish this by:
		using coefficient data at an angle of attack that is 20.08% of actual (stall alpha=  67.23 deg),
		and reducing airfoil lift coefficients to            60.04% of their 2-D value.
		Based on AR and sweep, cm change is to               3.04% of the 2-D value.
		Based on AR and TR, aerodynamic center is moved      34.73% of the way from the the 25% chord to the 50% chord.

Finite-Wing & Element Build-Up for ENG PYLN 4a :
	root lo Re: alphamax=  13.50 deg, trat= 0.0900, Re= 0.0000 meg for NACA 0009 (symmetrical).afl.
	root hi Re: alphamax=  13.50 deg, trat= 0.0900, Re=99.9000 meg for NACA 0009 (symmetrical).afl.
	tip  lo Re: alphamax=  13.50 deg, trat= 0.0900, Re= 0.0000 meg for NACA 0009 (symmetrical).afl.
	tip  hi Re: alphamax=  13.50 deg, trat= 0.0900, Re=99.9000 meg for NACA 0009 (symmetrical).afl.
	Element # 1: S=   7.302 sqr mtrs, MAC=   6.70 mtrs, incidence=   0.00 deg.
	Applying biplane interference factor to Oswalds Efficiency! between ENG PYLN 4a  and ENG PYLN 3a 
	After any wing-joining, our semi-length        is     4.51 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our root chord         is     7.99 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our tip chord          is     5.21 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our leading-edge sweep is    77.68 deg.  (for purposes of                        Delta-Wing factor determination only)
	After any wing-joining, our mean aero	 sweep is    75.80 deg.  (for purposes of Oswalds Efficiency                       determination only)
	After any wing-joining, our aspect ratio       is     0.50.      (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our taper ratio        is     0.65.      (for purposes of Oswalds Efficiency and Delta-Wing factor determination only)
	After any wing-joining, our washout            is     0.00 deg.  (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root=    0.00 deg, tip=    0.00 deg)
	Oswalds efficiency is therefore  0.5000, for lift-slope reduction to 12.06% of the 2-D value.
	We will accomplish this by:
		using coefficient data at an angle of attack that is 20.08% of actual (stall alpha=  67.23 deg),
		and reducing airfoil lift coefficients to            60.04% of their 2-D value.
		Based on AR and sweep, cm change is to               3.04% of the 2-D value.
		Based on AR and TR, aerodynamic center is moved      34.73% of the way from the the 25% chord to the 50% chord.


Now for MI from FUSELAGE    :
The frontal area                is   38.451 square meters.
The side area                   is  422.078 square meters.
The top area                    is  370.666 square meters.
The RUNNING TOTAL wetted area   is 1661.427 square meters.
The longitudinal centroid       is    2.773 meters.
The lateral      centroid       is    0.000 meters.
The vertical     centroid       is    1.121 meters.
The radius of gyration in roll  is    0.00 meters.
The radius of gyration in pitch is    0.00 meters.
The radius of gyration in yaw   is    0.00 meters.


Now for MI from MISC BODY 1 :
The frontal area                is   29.832 square meters.
The side area                   is  135.500 square meters.
The top area                    is  172.690 square meters.
The RUNNING TOTAL wetted area   is 2189.924 square meters.
The longitudinal centroid       is    0.189 meters.
The lateral      centroid       is    0.000 meters.
The vertical     centroid       is   -0.589 meters.
The radius of gyration in roll  is    0.00 meters.
The radius of gyration in pitch is    0.00 meters.
The radius of gyration in yaw   is    0.00 meters.


Now for MI from MISC BODY 2 :
The frontal area                is    0.407 square meters.
The side area                   is    0.598 square meters.
The top area                    is    0.791 square meters.
The RUNNING TOTAL wetted area   is 2193.342 square meters.
The longitudinal centroid       is  -20.626 meters.
The lateral      centroid       is    0.000 meters.
The vertical     centroid       is   -1.836 meters.
The radius of gyration in roll  is    0.00 meters.
The radius of gyration in pitch is    0.00 meters.
The radius of gyration in yaw   is    0.00 meters.


Now for MI from MISC BODY 3 :
The frontal area                is    0.056 square meters.
The side area                   is    0.067 square meters.
The top area                    is    0.181 square meters.
The RUNNING TOTAL wetted area   is 2194.182 square meters.
The longitudinal centroid       is  -20.319 meters.
The lateral      centroid       is    0.000 meters.
The vertical     centroid       is   -1.874 meters.
The radius of gyration in roll  is    0.00 meters.
The radius of gyration in pitch is    0.00 meters.
The radius of gyration in yaw   is    0.00 meters.


Now for MI from MISC BODY 4 :
The frontal area                is    0.104 square meters.
The side area                   is    0.100 square meters.
The top area                    is    0.269 square meters.
The RUNNING TOTAL wetted area   is 2194.909 square meters.
The longitudinal centroid       is    2.266 meters.
The lateral      centroid       is    0.000 meters.
The vertical     centroid       is    4.141 meters.
The radius of gyration in roll  is    0.00 meters.
The radius of gyration in pitch is    0.00 meters.
The radius of gyration in yaw   is    0.00 meters.


Now for MI from MISC BODY 5 :
The frontal area                is    0.104 square meters.
The side area                   is    0.100 square meters.
The top area                    is    0.269 square meters.
The RUNNING TOTAL wetted area   is 2195.637 square meters.
The longitudinal centroid       is    3.150 meters.
The lateral      centroid       is    0.000 meters.
The vertical     centroid       is    4.141 meters.
The radius of gyration in roll  is    0.00 meters.
The radius of gyration in pitch is    0.00 meters.
The radius of gyration in yaw   is    0.00 meters.


Now for MI from MISC BODY 6 :
The frontal area                is    0.120 square meters.
The side area                   is    0.903 square meters.
The top area                    is    1.124 square meters.
The RUNNING TOTAL wetted area   is 2199.614 square meters.
The longitudinal centroid       is    3.480 meters.
The lateral      centroid       is    5.188 meters.
The vertical     centroid       is   -1.601 meters.
The radius of gyration in roll  is    0.00 meters.
The radius of gyration in pitch is    0.00 meters.
The radius of gyration in yaw   is    0.00 meters.


Now for MI from MISC BODY 7 :
The frontal area                is    0.120 square meters.
The side area                   is    0.903 square meters.
The top area                    is    1.124 square meters.
The RUNNING TOTAL wetted area   is 2203.591 square meters.
The longitudinal centroid       is    3.480 meters.
The lateral      centroid       is   -5.188 meters.
The vertical     centroid       is   -1.601 meters.
The radius of gyration in roll  is    0.00 meters.
The radius of gyration in pitch is    0.00 meters.
The radius of gyration in yaw   is    0.00 meters.


Now for MI from MISC BODY 8 :
The frontal area                is    0.015 square meters.
The side area                   is    0.118 square meters.
The top area                    is    0.115 square meters.
The RUNNING TOTAL wetted area   is 2203.961 square meters.
The longitudinal centroid       is   17.762 meters.
The lateral      centroid       is  -28.529 meters.
The vertical     centroid       is    1.586 meters.
The radius of gyration in roll  is    0.00 meters.
The radius of gyration in pitch is    0.00 meters.
The radius of gyration in yaw   is    0.00 meters.


Now for MI from MISC BODY 9 :
The frontal area                is    0.015 square meters.
The side area                   is    0.118 square meters.
The top area                    is    0.115 square meters.
The RUNNING TOTAL wetted area   is 2204.331 square meters.
The longitudinal centroid       is   17.762 meters.
The lateral      centroid       is   28.529 meters.
The vertical     centroid       is    1.586 meters.
The radius of gyration in roll  is    0.00 meters.
The radius of gyration in pitch is    0.00 meters.
The radius of gyration in yaw   is    0.00 meters.


Now for MI from MISC BODY 10:
The frontal area                is    0.344 square meters.
The side area                   is    0.460 square meters.
The top area                    is    0.870 square meters.
The RUNNING TOTAL wetted area   is 2207.796 square meters.
The longitudinal centroid       is   38.670 meters.
The lateral      centroid       is    0.000 meters.
The vertical     centroid       is    3.065 meters.
The radius of gyration in roll  is    0.00 meters.
The radius of gyration in pitch is    0.00 meters.
The radius of gyration in yaw   is    0.00 meters.


Now for MI from MISC BODY 11:
The frontal area                is    0.007 square meters.
The side area                   is    0.115 square meters.
The top area                    is    0.114 square meters.
The RUNNING TOTAL wetted area   is 2208.176 square meters.
The longitudinal centroid       is  -20.914 meters.
The lateral      centroid       is   -0.671 meters.
The vertical     centroid       is   -1.796 meters.
The radius of gyration in roll  is    0.00 meters.
The radius of gyration in pitch is    0.00 meters.
The radius of gyration in yaw   is    0.00 meters.


Now for MI from MISC BODY 12:
The frontal area                is    0.007 square meters.
The side area                   is    0.115 square meters.
The top area                    is    0.114 square meters.
The RUNNING TOTAL wetted area   is 2208.556 square meters.
The longitudinal centroid       is  -20.914 meters.
The lateral      centroid       is    0.671 meters.
The vertical     centroid       is   -1.796 meters.
The radius of gyration in roll  is    0.00 meters.
The radius of gyration in pitch is    0.00 meters.
The radius of gyration in yaw   is    0.00 meters.


Now for MI from MISC BODY 13:
The frontal area                is    0.129 square meters.
The side area                   is    0.409 square meters.
The top area                    is    0.653 square meters.
The RUNNING TOTAL wetted area   is 2210.502 square meters.
The longitudinal centroid       is   10.335 meters.
The lateral      centroid       is    0.000 meters.
The vertical     centroid       is    4.152 meters.
The radius of gyration in roll  is    0.00 meters.
The radius of gyration in pitch is    0.00 meters.
The radius of gyration in yaw   is    0.00 meters.


Now for MI from MISC BODY 17:
The frontal area                is    3.095 square meters.
The side area                   is    2.067 square meters.
The top area                    is    2.074 square meters.
The RUNNING TOTAL wetted area   is 2220.178 square meters.
The longitudinal centroid       is  -28.417 meters.
The lateral      centroid       is    0.000 meters.
The vertical     centroid       is    0.787 meters.
The radius of gyration in roll  is    0.00 meters.
The radius of gyration in pitch is    0.00 meters.
The radius of gyration in yaw   is    0.00 meters.


Now for MI from MISC BODY 18:
The frontal area                is    0.016 square meters.
The side area                   is    0.040 square meters.
The top area                    is    0.038 square meters.
The RUNNING TOTAL wetted area   is 2220.322 square meters.
The longitudinal centroid       is  -15.817 meters.
The lateral      centroid       is    0.000 meters.
The vertical     centroid       is    5.138 meters.
The radius of gyration in roll  is    0.00 meters.
The radius of gyration in pitch is    0.00 meters.
The radius of gyration in yaw   is    0.00 meters.


Now for MI from MISC BODY 19:
The frontal area                is    0.004 square meters.
The side area                   is    0.015 square meters.
The top area                    is    0.023 square meters.
The RUNNING TOTAL wetted area   is 2220.385 square meters.
The longitudinal centroid       is  -20.116 meters.
The lateral      centroid       is    0.000 meters.
The vertical     centroid       is    5.135 meters.
The radius of gyration in roll  is    0.00 meters.
The radius of gyration in pitch is    0.00 meters.
The radius of gyration in yaw   is    0.00 meters.


Now for MI from NACELLE 1   :
The frontal area                is    7.464 square meters.
The side area                   is   20.010 square meters.
The top area                    is   23.548 square meters.
The RUNNING TOTAL wetted area   is 2304.761 square meters.
The longitudinal centroid       is    5.284 meters.
The lateral      centroid       is  -21.062 meters.
The vertical     centroid       is   -1.513 meters.
The radius of gyration in roll  is    0.00 meters.
The radius of gyration in pitch is    0.00 meters.
The radius of gyration in yaw   is    0.00 meters.


Now for MI from NACELLE 2   :
The frontal area                is    7.464 square meters.
The side area                   is   20.010 square meters.
The top area                    is   23.548 square meters.
The RUNNING TOTAL wetted area   is 2389.138 square meters.
The longitudinal centroid       is   -3.799 meters.
The lateral      centroid       is  -11.918 meters.
The vertical     centroid       is   -2.397 meters.
The radius of gyration in roll  is    0.00 meters.
The radius of gyration in pitch is    0.00 meters.
The radius of gyration in yaw   is    0.00 meters.


Now for MI from NACELLE 3   :
The frontal area                is    7.464 square meters.
The side area                   is   20.010 square meters.
The top area                    is   23.548 square meters.
The RUNNING TOTAL wetted area   is 2473.514 square meters.
The longitudinal centroid       is   -3.799 meters.
The lateral      centroid       is   11.918 meters.
The vertical     centroid       is   -2.397 meters.
The radius of gyration in roll  is    0.00 meters.
The radius of gyration in pitch is    0.00 meters.
The radius of gyration in yaw   is    0.00 meters.


Now for MI from NACELLE 4   :
The frontal area                is    7.464 square meters.
The side area                   is   20.010 square meters.
The top area                    is   23.548 square meters.
The RUNNING TOTAL wetted area   is 2557.890 square meters.
The longitudinal centroid       is    5.284 meters.
The lateral      centroid       is   21.062 meters.
The vertical     centroid       is   -1.513 meters.
The radius of gyration in roll  is    0.00 meters.
The radius of gyration in pitch is    0.00 meters.
The radius of gyration in yaw   is    0.00 meters.


Now for MI from W-FAIRING 1 :
The frontal area                is    0.112 square meters.
The side area                   is    0.121 square meters.
The top area                    is    0.325 square meters.
The RUNNING TOTAL wetted area   is 2559.376 square meters.
The longitudinal centroid       is  -21.689 meters.
The lateral      centroid       is    0.000 meters.
The vertical     centroid       is   -4.137 meters.
The radius of gyration in roll  is    0.00 meters.
The radius of gyration in pitch is    0.00 meters.
The radius of gyration in yaw   is    0.00 meters.


Now for MI from W-FAIRING 2 :
The frontal area                is    0.071 square meters.
The side area                   is    0.378 square meters.
The top area                    is    0.517 square meters.
The RUNNING TOTAL wetted area   is 2561.284 square meters.
The longitudinal centroid       is    5.470 meters.
The lateral      centroid       is    1.887 meters.
The vertical     centroid       is   -4.230 meters.
The radius of gyration in roll  is    0.00 meters.
The radius of gyration in pitch is    0.00 meters.
The radius of gyration in yaw   is    0.00 meters.


Now for MI from W-FAIRING 3 :
The frontal area                is    0.071 square meters.
The side area                   is    0.378 square meters.
The top area                    is    0.517 square meters.
The RUNNING TOTAL wetted area   is 2563.191 square meters.
The longitudinal centroid       is    5.470 meters.
The lateral      centroid       is   -1.887 meters.
The vertical     centroid       is   -4.230 meters.
The radius of gyration in roll  is    0.00 meters.
The radius of gyration in pitch is    0.00 meters.
The radius of gyration in yaw   is    0.00 meters.


Now for MI from W-FAIRING 4 :
The frontal area                is    0.071 square meters.
The side area                   is    0.378 square meters.
The top area                    is    0.517 square meters.
The RUNNING TOTAL wetted area   is 2565.099 square meters.
The longitudinal centroid       is    2.381 meters.
The lateral      centroid       is    5.188 meters.
The vertical     centroid       is   -4.233 meters.
The radius of gyration in roll  is    0.00 meters.
The radius of gyration in pitch is    0.00 meters.
The radius of gyration in yaw   is    0.00 meters.


Now for MI from W-FAIRING 5 :
The frontal area                is    0.071 square meters.
The side area                   is    0.378 square meters.
The top area                    is    0.517 square meters.
The RUNNING TOTAL wetted area   is 2567.007 square meters.
The longitudinal centroid       is    2.381 meters.
The lateral      centroid       is   -5.188 meters.
The vertical     centroid       is   -4.233 meters.
The radius of gyration in roll  is    0.00 meters.
The radius of gyration in pitch is    0.00 meters.
The radius of gyration in yaw   is    0.00 meters.

Engines have mass 20672.93 kg (5.21% of total):
	The radius of gyration of the engines in roll is    17.23 m, based on all engine powers/thrusts and locations.
	The radius of gyration of the engines in pitch is    6.74 m, based on all engine powers/thrusts and locations.
	The radius of gyration of the engines in yaw is     18.28 m, based on all engine powers/thrusts and locations.

Remainder of the craft has mass 158082.42 (39.83% of total):
	The radius of gyration of the shell	in roll is     8.61 m, based on mass-distribution across the shell of the craft with a 50% weighting on all of the flying surfaces.
	The radius of gyration of the shell	in pitch is   15.32 m, based on mass-distribution across the shell of the craft with a 50% weighting on all of the flying surfaces.
	The radius of gyration of the shell	in yaw is     17.21 m, based on mass-distribution across the shell of the craft with a 50% weighting on all of the flying surfaces.

Final combined results:
	The radius of gyration in roll is    10.00 m.
	The radius of gyration in pitch is   14.59 m.
	The radius of gyration in yaw is     17.33 m.

For LEFT WING 1 :
Full slat deployment will cause coefficient data to spread out alpha-wise to 142.49% of original.
Full slat deployment will also change the lift coefficient by the same amount (keeping the lift SLOPE the same).

For RIGT WING 1 :
Full slat deployment will cause coefficient data to spread out alpha-wise to 142.49% of original.
Full slat deployment will also change the lift coefficient by the same amount (keeping the lift SLOPE the same).

For LEFT WING 2 :
Full slat deployment will cause coefficient data to spread out alpha-wise to 142.49% of original.
Full slat deployment will also change the lift coefficient by the same amount (keeping the lift SLOPE the same).

For RIGT WING 2 :
Full slat deployment will cause coefficient data to spread out alpha-wise to 142.49% of original.
Full slat deployment will also change the lift coefficient by the same amount (keeping the lift SLOPE the same).

For LEFT WING 3 :
Full slat deployment will cause coefficient data to spread out alpha-wise to 142.49% of original.
Full slat deployment will also change the lift coefficient by the same amount (keeping the lift SLOPE the same).

For RIGT WING 3 :
Full slat deployment will cause coefficient data to spread out alpha-wise to 142.49% of original.
Full slat deployment will also change the lift coefficient by the same amount (keeping the lift SLOPE the same).

For LEFT WING 4 :
Full slat deployment will cause coefficient data to spread out alpha-wise to 142.49% of original.
Full slat deployment will also change the lift coefficient by the same amount (keeping the lift SLOPE the same).

For RIGT WING 4 :
Full slat deployment will cause coefficient data to spread out alpha-wise to 142.49% of original.
Full slat deployment will also change the lift coefficient by the same amount (keeping the lift SLOPE the same).


The centroid of all foils is at          9.70 m (positive aft from CG) when the 25% chord is assumed to be the element location.
The centroid of all foils is at         10.26 m (positive aft from CG) when the wing is looked at partially as a delta-wing based on taper ratio.
The average chord of all foils is        7.22 m.
So you could say the static margin is    1.34 (positive stable) when the 25% chord is assumed to be the element location.
So you could say the static margin is    1.42 (positive stable) when the wing is looked at partially as a delta-wing based on taper ratio.

There will be downwash from the LEFT WING 1  onto the LEFT WING 2  element # 0, with a spanwise coverage of   0%
There will be downwash from the RIGT WING 1  onto the RIGT WING 2  element # 0, with a spanwise coverage of   0%
There will be downwash from the LEFT WING 2  onto the LEFT WING 3  element # 0, with a spanwise coverage of   2%
There will be downwash from the RIGT WING 2  onto the RIGT WING 3  element # 0, with a spanwise coverage of   2%
There will be downwash from the LEFT WING 3  onto the LEFT WING 4  element # 0, with a spanwise coverage of   0%
There will be downwash from the RIGT WING 3  onto the RIGT WING 4  element # 0, with a spanwise coverage of   0%
There will be downwash from the LEFT WING 1  onto the LEFT H-STAB  element # 0, with a spanwise coverage of 100%
There will be downwash from the LEFT WING 1  onto the LEFT H-STAB  element # 1, with a spanwise coverage of 100%
There will be downwash from the LEFT WING 1  onto the LEFT H-STAB  element # 2, with a spanwise coverage of 100%
There will be downwash from the LEFT WING 1  onto the LEFT H-STAB  element # 3, with a spanwise coverage of 100%
There will be downwash from the LEFT WING 1  onto the LEFT H-STAB  element # 4, with a spanwise coverage of 100%
There will be downwash from the LEFT WING 1  onto the LEFT H-STAB  element # 5, with a spanwise coverage of 100%
There will be downwash from the LEFT WING 1  onto the LEFT H-STAB  element # 6, with a spanwise coverage of 100%
There will be downwash from the RIGT WING 1  onto the RIGT H-STAB  element # 0, with a spanwise coverage of 100%
There will be downwash from the RIGT WING 1  onto the RIGT H-STAB  element # 1, with a spanwise coverage of 100%
There will be downwash from the RIGT WING 1  onto the RIGT H-STAB  element # 2, with a spanwise coverage of 100%
There will be downwash from the RIGT WING 1  onto the RIGT H-STAB  element # 3, with a spanwise coverage of 100%
There will be downwash from the RIGT WING 1  onto the RIGT H-STAB  element # 4, with a spanwise coverage of 100%
There will be downwash from the RIGT WING 1  onto the RIGT H-STAB  element # 5, with a spanwise coverage of 100%
There will be downwash from the RIGT WING 1  onto the RIGT H-STAB  element # 6, with a spanwise coverage of 100%
For washing LEFT WING 1  onto the LEFT WING 2 , AR= 7.0517, TR= 0.2000, dz=   8.60 m, dy=   1.19 m, mac=  13.19, subsonic wash will be    1.95 and supersonic wash will be    0.04 deg per coefficient of lift TIMES THE COSINE of the LEFT WING 1  sweep.
For washing RIGT WING 1  onto the RIGT WING 2 , AR= 7.0537, TR= 0.2000, dz=   8.60 m, dy=   1.19 m, mac=  13.19, subsonic wash will be    1.95 and supersonic wash will be    0.04 deg per coefficient of lift TIMES THE COSINE of the RIGT WING 1  sweep.
For washing LEFT WING 2  onto the LEFT WING 3 , AR= 7.0517, TR= 0.2000, dz=   1.34 m, dy=   0.18 m, mac=   9.34, subsonic wash will be    1.97 and supersonic wash will be    0.04 deg per coefficient of lift TIMES THE COSINE of the LEFT WING 2  sweep.
For washing RIGT WING 2  onto the RIGT WING 3 , AR= 7.0537, TR= 0.2000, dz=   1.34 m, dy=   0.18 m, mac=   9.34, subsonic wash will be    1.97 and supersonic wash will be    0.04 deg per coefficient of lift TIMES THE COSINE of the RIGT WING 2  sweep.
For washing LEFT WING 3  onto the LEFT WING 4 , AR= 7.0517, TR= 0.2000, dz=   7.50 m, dy=   0.90 m, mac=   7.36, subsonic wash will be    1.94 and supersonic wash will be    0.04 deg per coefficient of lift TIMES THE COSINE of the LEFT WING 3  sweep.
For washing RIGT WING 3  onto the RIGT WING 4 , AR= 7.0537, TR= 0.2000, dz=   7.50 m, dy=   0.90 m, mac=   7.36, subsonic wash will be    1.94 and supersonic wash will be    0.04 deg per coefficient of lift TIMES THE COSINE of the RIGT WING 3  sweep.
For washing LEFT WING 1  onto the LEFT H-STAB , AR= 7.0517, TR= 0.2000, dz=  37.64 m, dy=   3.78 m, mac=  13.19, subsonic wash will be    2.94 and supersonic wash will be    0.07 deg per coefficient of lift TIMES THE COSINE of the LEFT WING 1  sweep.
For washing RIGT WING 1  onto the RIGT H-STAB , AR= 7.0537, TR= 0.2000, dz=  37.64 m, dy=   3.78 m, mac=  13.19, subsonic wash will be    2.94 and supersonic wash will be    0.07 deg per coefficient of lift TIMES THE COSINE of the RIGT WING 1  sweep.
