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X-Plane, by Austin Meyer
122010
Simulating Aircraft/Laminar Research/Van's Aircraft RV-10/RV-10.acf
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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 and build-up for prop 1: Wing area for this wing is  0.1301 m*m.
	After any wing-joining, our area            is    0.13 m*m.
	After any wing-joining, our semi-length     is    0.98 m.
	After any wing-joining, our root chord      is    0.18 m.
	After any wing-joining, our tip chord       is    0.09 m.
	After any wing-joining, our mean aero sweep is    0.0 deg.
	After any wing-joining, our aspect ratio    is 14.6286.
	After any wing-joining, spanwise centroid   is  0.4450 semi-spans. (this is area centroid fraction of the way out to the tip)
	After any wing-joining, our taper ratio     is  0.6765.
	Oswalds efficiency is therefore  0.9471.

Finite-wing and build-up for Right Wing 1: Wing area for this wing is  6.1368 m*m.
	NOTE! I AM ADDING Right Wing 2 TO THE TIP OF Right Wing 1 (through any intermediate wings) TO FORM ONE CONTINUOUS WING! (S=6.6643 m*m, connecting at x=-4.3688, y=-0.1595, z=0.1829, loop=0/48)
	After any wing-joining, our area            is    6.66 m*m.
	After any wing-joining, our semi-length     is    4.85 m.
	After any wing-joining, our root chord      is    1.40 m.
	After any wing-joining, our tip chord       is    0.76 m.
	After any wing-joining, our mean aero sweep is    5.7 deg.
	After any wing-joining, our aspect ratio    is  6.9834.
	After any wing-joining, spanwise centroid   is  0.4930 semi-spans. (this is area centroid fraction of the way out to the tip)
	After any wing-joining, our taper ratio     is  0.9587.
	Oswalds efficiency is therefore  0.9527.

Finite-wing and build-up for Right Wing 1: Wing area for this wing is  6.1368 m*m.
	NOTE! I AM ADDING Right Wing 2 TO THE TIP OF Right Wing 1 (through any intermediate wings) TO FORM ONE CONTINUOUS WING! (S=6.6643 m*m, connecting at x=4.3688, y=-0.1595, z=0.1829, loop=0/48)
	After any wing-joining, our area            is    6.66 m*m.
	After any wing-joining, our semi-length     is    4.85 m.
	After any wing-joining, our root chord      is    1.40 m.
	After any wing-joining, our tip chord       is    0.76 m.
	After any wing-joining, our mean aero sweep is    5.7 deg.
	After any wing-joining, our aspect ratio    is  6.9834.
	After any wing-joining, spanwise centroid   is  0.4930 semi-spans. (this is area centroid fraction of the way out to the tip)
	After any wing-joining, our taper ratio     is  0.9587.
	Oswalds efficiency is therefore  0.9527.

Finite-wing and build-up for Right Wing 2: Wing area for this wing is  0.5275 m*m.
	NOTE! I AM ADDING Right Wing 1 TO THE ROOT OF Right Wing 2 (through any intermediate wings) TO FORM ONE CONTINUOUS WING! (S=6.6643 m*m, connecting at x=-4.3688, y=-0.1595, z=0.1829, loop=0/48)
	After any wing-joining, our area            is    6.66 m*m.
	After any wing-joining, our semi-length     is    4.85 m.
	After any wing-joining, our root chord      is    1.40 m.
	After any wing-joining, our tip chord       is    0.76 m.
	After any wing-joining, our mean aero sweep is    5.7 deg.
	After any wing-joining, our aspect ratio    is  6.9834.
	After any wing-joining, spanwise centroid   is  0.4930 semi-spans. (this is area centroid fraction of the way out to the tip)
	After any wing-joining, our taper ratio     is  0.9587.
	Oswalds efficiency is therefore  0.9527.

Finite-wing and build-up for Right Wing 2: Wing area for this wing is  0.5275 m*m.
	NOTE! I AM ADDING Right Wing 1 TO THE ROOT OF Right Wing 2 (through any intermediate wings) TO FORM ONE CONTINUOUS WING! (S=6.6643 m*m, connecting at x=4.3688, y=-0.1595, z=0.1829, loop=0/48)
	After any wing-joining, our area            is    6.66 m*m.
	After any wing-joining, our semi-length     is    4.85 m.
	After any wing-joining, our root chord      is    1.40 m.
	After any wing-joining, our tip chord       is    0.76 m.
	After any wing-joining, our mean aero sweep is    5.7 deg.
	After any wing-joining, our aspect ratio    is  6.9834.
	After any wing-joining, spanwise centroid   is  0.4930 semi-spans. (this is area centroid fraction of the way out to the tip)
	After any wing-joining, our taper ratio     is  0.9587.
	Oswalds efficiency is therefore  0.9527.

Finite-wing and build-up for Right Stab: Wing area for this wing is  1.7001 m*m.
	After any wing-joining, our area            is    1.70 m*m.
	After any wing-joining, our semi-length     is    1.86 m.
	After any wing-joining, our root chord      is    0.91 m.
	After any wing-joining, our tip chord       is    0.91 m.
	After any wing-joining, our mean aero sweep is    0.0 deg.
	After any wing-joining, our aspect ratio    is  4.0667.
	After any wing-joining, spanwise centroid   is  0.5000 semi-spans. (this is area centroid fraction of the way out to the tip)
	After any wing-joining, our taper ratio     is  1.0000.
	Oswalds efficiency is therefore  0.9731.

Finite-wing and build-up for Right Stab: Wing area for this wing is  1.7001 m*m.
	After any wing-joining, our area            is    1.70 m*m.
	After any wing-joining, our semi-length     is    1.86 m.
	After any wing-joining, our root chord      is    0.91 m.
	After any wing-joining, our tip chord       is    0.91 m.
	After any wing-joining, our mean aero sweep is    0.0 deg.
	After any wing-joining, our aspect ratio    is  4.0667.
	After any wing-joining, spanwise centroid   is  0.5000 semi-spans. (this is area centroid fraction of the way out to the tip)
	After any wing-joining, our taper ratio     is  1.0000.
	Oswalds efficiency is therefore  0.9731.

Finite-wing and build-up for Vert Stab 1: Wing area for this wing is  1.9296 m*m.
	After any wing-joining, our area            is    1.93 m*m.
	After any wing-joining, our semi-length     is    1.74 m.
	After any wing-joining, our root chord      is    1.58 m.
	After any wing-joining, our tip chord       is    0.67 m.
	After any wing-joining, our mean aero sweep is   10.0 deg.
	After any wing-joining, our aspect ratio    is  3.0343.
	After any wing-joining, spanwise centroid   is  0.4367 semi-spans. (this is area centroid fraction of the way out to the tip)
	After any wing-joining, our taper ratio     is  0.6274.
	Oswalds efficiency is therefore  0.9968.


The prop 1 DISC AREA is broken down into rings for propwash distribution as follows:
	element number  0, rad1=   0.00, rad2=   0.10, ring area is  0.0299 m*m.
	element number  1, rad1=   0.10, rad2=   0.20, ring area is  0.0897 m*m.
	element number  2, rad1=   0.20, rad2=   0.29, ring area is  0.1494 m*m.
	element number  3, rad1=   0.29, rad2=   0.39, ring area is  0.2092 m*m.
	element number  4, rad1=   0.39, rad2=   0.49, ring area is  0.2690 m*m.
	element number  5, rad1=   0.49, rad2=   0.59, ring area is  0.3288 m*m.
	element number  6, rad1=   0.59, rad2=   0.68, ring area is  0.3885 m*m.
	element number  7, rad1=   0.68, rad2=   0.78, ring area is  0.4483 m*m.
	element number  8, rad1=   0.78, rad2=   0.88, ring area is  0.5081 m*m.
	element number  9, rad1=   0.88, rad2=   0.98, ring area is  0.5678 m*m.
	TOTAL DISC AREA= 2.9887 m*m
	en=0, el=0, element_mass=  0.712 veh_prop_ptr(en)->prop_mass=0.712, rad_arm_mtr=   0.07, veh_prop_ptr(en)->prop_mi_rpm=  0.003 kg*m*m
	en=0, el=1, element_mass=  0.641 veh_prop_ptr(en)->prop_mass=1.354, rad_arm_mtr=   0.17, veh_prop_ptr(en)->prop_mi_rpm=  0.021 kg*m*m
	en=0, el=2, element_mass=  0.574 veh_prop_ptr(en)->prop_mass=1.927, rad_arm_mtr=   0.26, veh_prop_ptr(en)->prop_mi_rpm=  0.061 kg*m*m
	en=0, el=3, element_mass=  0.510 veh_prop_ptr(en)->prop_mass=2.438, rad_arm_mtr=   0.36, veh_prop_ptr(en)->prop_mi_rpm=  0.128 kg*m*m
	en=0, el=4, element_mass=  0.450 veh_prop_ptr(en)->prop_mass=2.888, rad_arm_mtr=   0.46, veh_prop_ptr(en)->prop_mi_rpm=  0.223 kg*m*m
	en=0, el=5, element_mass=  0.394 veh_prop_ptr(en)->prop_mass=3.282, rad_arm_mtr=   0.56, veh_prop_ptr(en)->prop_mi_rpm=  0.345 kg*m*m
	en=0, el=6, element_mass=  0.342 veh_prop_ptr(en)->prop_mass=3.623, rad_arm_mtr=   0.65, veh_prop_ptr(en)->prop_mi_rpm=  0.491 kg*m*m
	en=0, el=7, element_mass=  0.293 veh_prop_ptr(en)->prop_mass=3.916, rad_arm_mtr=   0.75, veh_prop_ptr(en)->prop_mi_rpm=  0.656 kg*m*m
	en=0, el=8, element_mass=  0.248 veh_prop_ptr(en)->prop_mass=4.164, rad_arm_mtr=   0.85, veh_prop_ptr(en)->prop_mi_rpm=  0.835 kg*m*m
	en=0, el=9, element_mass=  0.207 veh_prop_ptr(en)->prop_mass=4.371, rad_arm_mtr=   0.95, veh_prop_ptr(en)->prop_mi_rpm=  1.020 kg*m*m
	BEFORE any tip weights, the prop 1 weighs   4.371 kg, and the MI is   1.020 kg*m*m
	 AFTER any tip weights, the prop 1 weighs   4.371 kg, and the MI is   1.020 kg*m*m

Critical altitude for prop engines=    0 ft, rho at crit alt= 1.2250 kg/mmm, rho at SL= 1.2250 kg/mmm, engine power boosted to  1.0000 of original, spinning motor MI 1.2126 kg*m*m

Engine # 0 is mass 167.466 kg at x=   0.00, y=   0.05, z=  -1.95 (for moment of inertia build-up)

Prop # 0 is mass   4.371 kg at x=   0.00,  y=   0.05,  z=  -1.95 (for moment of inertia build-up)

Fuel tank # 0 is mass   4.309 kg at x=  -1.83,  y=  -0.26,  z=   0.02 (for moment of inertia build-up)
Fuel tank # 1 is mass   4.309 kg at x=   1.83,  y=  -0.26,  z=   0.02 (for moment of inertia build-up)

Right Wing 1 Running wetted area  1.9638 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     2.63 m, based on mass-distribution across the shell of the craft with the 0.12 thickness wing giving a 0.16 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in pitch is    0.35 m, based on mass-distribution across the shell of the craft with the 0.12 thickness wing giving a 0.16 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in yaw is      2.62 m, based on mass-distribution across the shell of the craft with the 0.12 thickness wing giving a 0.16 weighting per square meter on this flying surface.

Right Wing 1 Running wetted area  3.9276 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     2.63 m, based on mass-distribution across the shell of the craft with the 0.12 thickness wing giving a 0.16 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in pitch is    0.35 m, based on mass-distribution across the shell of the craft with the 0.12 thickness wing giving a 0.16 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in yaw is      2.62 m, based on mass-distribution across the shell of the craft with the 0.12 thickness wing giving a 0.16 weighting per square meter on this flying surface.

Right Wing 2 Running wetted area  4.0963 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     2.74 m, based on mass-distribution across the shell of the craft with the 0.12 thickness wing giving a 0.16 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in pitch is    0.35 m, based on mass-distribution across the shell of the craft with the 0.12 thickness wing giving a 0.16 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in yaw is      2.73 m, based on mass-distribution across the shell of the craft with the 0.12 thickness wing giving a 0.16 weighting per square meter on this flying surface.

Right Wing 2 Running wetted area  4.2651 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     2.84 m, based on mass-distribution across the shell of the craft with the 0.12 thickness wing giving a 0.16 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in pitch is    0.35 m, based on mass-distribution across the shell of the craft with the 0.12 thickness wing giving a 0.16 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in yaw is      2.83 m, based on mass-distribution across the shell of the craft with the 0.12 thickness wing giving a 0.16 weighting per square meter on this flying surface.

Right Stab Running wetted area  4.7582 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     2.72 m, based on mass-distribution across the shell of the craft with the 0.09 thickness wing giving a 0.14 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in pitch is    1.38 m, based on mass-distribution across the shell of the craft with the 0.09 thickness wing giving a 0.14 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in yaw is      3.02 m, based on mass-distribution across the shell of the craft with the 0.09 thickness wing giving a 0.14 weighting per square meter on this flying surface.

Right Stab Running wetted area  5.2512 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     2.61 m, based on mass-distribution across the shell of the craft with the 0.09 thickness wing giving a 0.14 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in pitch is    1.83 m, based on mass-distribution across the shell of the craft with the 0.09 thickness wing giving a 0.14 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in yaw is      3.16 m, based on mass-distribution across the shell of the craft with the 0.09 thickness wing giving a 0.14 weighting per square meter on this flying surface.

Vert Stab 1 Running wetted area  5.8108 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     2.50 m, based on mass-distribution across the shell of the craft with the 0.09 thickness wing giving a 0.14 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in pitch is    2.19 m, based on mass-distribution across the shell of the craft with the 0.09 thickness wing giving a 0.14 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in yaw is      3.27 m, based on mass-distribution across the shell of the craft with the 0.09 thickness wing giving a 0.14 weighting per square meter on this flying surface.


Body 1 (fuselage):
	The frontal      area                          is  1.5308 m*m.
	The side         area                          is  5.7691 m*m.
	The top          area                          is  5.6597 m*m.
	The lateral      centroid                      is    0.00 m.
	The vertical     centroid                      is    0.07 m.
	The longitudinal centroid for lift at   0 slip is   -0.87 m.
	The longitudinal centroid for lift at 180 slip is    2.42 meters

	Running wetted area 25.2353 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     1.29 m, based on mass-distribution across the shell of the craft.
	Running radius of gyration of the shell in pitch is    1.91 m, based on mass-distribution across the shell of the craft.
	Running radius of gyration of the shell in yaw is      2.24 m, based on mass-distribution across the shell of the craft.

Body 30 (Front Wheel Fairing):
	The frontal      area                          is  0.0799 m*m.
	The side         area                          is  0.1980 m*m.
	The top          area                          is  0.1820 m*m.
	The lateral      centroid                      is    0.00 m.
	The vertical     centroid                      is    0.04 m.
	The longitudinal centroid for lift at   0 slip is   -0.13 m.
	The longitudinal centroid for lift at 180 slip is    0.26 meters

	Running wetted area 25.8874 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     1.29 m, based on mass-distribution across the shell of the craft.
	Running radius of gyration of the shell in pitch is    1.90 m, based on mass-distribution across the shell of the craft.
	Running radius of gyration of the shell in yaw is      2.22 m, based on mass-distribution across the shell of the craft.

Body 31 (Right Wheel Fairing ):
	The frontal      area                          is  0.0799 m*m.
	The side         area                          is  0.1980 m*m.
	The top          area                          is  0.1820 m*m.
	The lateral      centroid                      is    0.00 m.
	The vertical     centroid                      is    0.04 m.
	The longitudinal centroid for lift at   0 slip is   -0.13 m.
	The longitudinal centroid for lift at 180 slip is    0.26 meters

	Running wetted area 26.5395 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     1.29 m, based on mass-distribution across the shell of the craft.
	Running radius of gyration of the shell in pitch is    1.89 m, based on mass-distribution across the shell of the craft.
	Running radius of gyration of the shell in yaw is      2.20 m, based on mass-distribution across the shell of the craft.

Body 32 (Left Wheel Fairing):
	The frontal      area                          is  0.0799 m*m.
	The side         area                          is  0.1980 m*m.
	The top          area                          is  0.1820 m*m.
	The lateral      centroid                      is    0.00 m.
	The vertical     centroid                      is    0.04 m.
	The longitudinal centroid for lift at   0 slip is   -0.13 m.
	The longitudinal centroid for lift at 180 slip is    0.26 meters

	Running wetted area 27.1917 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     1.29 m, based on mass-distribution across the shell of the craft.
	Running radius of gyration of the shell in pitch is    1.87 m, based on mass-distribution across the shell of the craft.
	Running radius of gyration of the shell in yaw is      2.18 m, based on mass-distribution across the shell of the craft.

Sum of all engines have mass of 167.47 kg ( 22% of total):
	The radius of gyration of the engines in roll is     0.05 m, based on all engine masses and locations.
	The radius of gyration of the engines in pitch is    1.95 m, based on all engine masses and locations.
	The radius of gyration of the engines in yaw is      1.95 m, based on all engine masses and locations.

Sum of all props have mass of 4.37 kg (  0% of total):
	The radius of gyration of the props in roll is     0.05 m, based on all prop masses and locations.
	The radius of gyration of the props in pitch is    1.95 m, based on all prop masses and locations.
	The radius of gyration of the props in yaw is      1.95 m, based on all prop masses and locations.

Sum of all tanks have mass of 8.62 kg (  1% of total):
	The radius of gyration of the tanks in roll is     1.85 m, based on all tank masses and locations.
	The radius of gyration of the tanks in pitch is    0.26 m, based on all tank masses and locations.
	The radius of gyration of the tanks in yaw is      1.83 m, based on all tank masses and locations.

Remainder of the craft has mass 590.65 ( 77% of total):
	The radius of gyration of the shell in roll is     1.29 m, based on mass-distribution across the shell of the craft.
	The radius of gyration of the shell in pitch is    1.87 m, based on mass-distribution across the shell of the craft.
	The radius of gyration of the shell in yaw is      2.18 m, based on mass-distribution across the shell of the craft.

Final combined results:
	The radius of gyration in roll is     1.15 m. (that's moment of inertia 1015.848 kg*m*m).
	The radius of gyration in pitch is    1.88 m. (that's moment of inertia 2726.617 kg*m*m).
	The radius of gyration in yaw is      2.13 m. (that's moment of inertia 3485.725 kg*m*m).

Wing area           : 13.3037 m*m. (For wings 1 through 4 only, each times the cosine of its' dihedral! This does not include stabilizers or misc wings!)
Wing MAC            :    1.39 m.   (For wings 1 through 4 only! This does not include stabilizers or misc wings!)
Long-arm of 25% MAC :    0.19 m.   (For wings 1 through 4 only! This does not include stabilizers or misc wings!)

••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••
X-Plane, by Austin Meyer
122010
Simulating Aircraft/DWSim F-16C/DWSim F-16C.acf
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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 and build-up for Right Wing 1: Wing area for this wing is  5.1264 m*m.
	NOTE! I AM ADDING Right Wing 2 TO THE TIP OF Right Wing 1 (through any intermediate wings) TO FORM ONE CONTINUOUS WING! (S=14.8001 m*m, connecting at x=-1.0879, y=-0.0305, z=-0.8984, loop=0/48)
	After any wing-joining, our area            is   14.80 m*m.
	After any wing-joining, our semi-length     is    6.05 m.
	After any wing-joining, our root chord      is   11.43 m.
	After any wing-joining, our tip chord       is    1.25 m.
	After any wing-joining, our mean aero sweep is   46.0 deg.
	After any wing-joining, our aspect ratio    is  2.3832.
	After any wing-joining, spanwise centroid   is  0.3385 semi-spans. (this is area centroid fraction of the way out to the tip)
	After any wing-joining, our taper ratio     is  0.0498.
	Oswalds efficiency is therefore  0.9591.

Finite-wing and build-up for Right Wing 1: Wing area for this wing is  5.1264 m*m.
	NOTE! I AM ADDING Right Wing 2 TO THE TIP OF Right Wing 1 (through any intermediate wings) TO FORM ONE CONTINUOUS WING! (S=14.8001 m*m, connecting at x=1.0879, y=-0.0305, z=-0.8984, loop=0/48)
	After any wing-joining, our area            is   14.80 m*m.
	After any wing-joining, our semi-length     is    6.05 m.
	After any wing-joining, our root chord      is   11.43 m.
	After any wing-joining, our tip chord       is    1.25 m.
	After any wing-joining, our mean aero sweep is   46.0 deg.
	After any wing-joining, our aspect ratio    is  2.3832.
	After any wing-joining, spanwise centroid   is  0.3385 semi-spans. (this is area centroid fraction of the way out to the tip)
	After any wing-joining, our taper ratio     is  0.0498.
	Oswalds efficiency is therefore  0.9591.

Finite-wing and build-up for Right Wing 2: Wing area for this wing is  9.6737 m*m.
	NOTE! I AM ADDING Right Wing 1 TO THE ROOT OF Right Wing 2 (through any intermediate wings) TO FORM ONE CONTINUOUS WING! (S=14.8001 m*m, connecting at x=-1.1095, y=-0.0305, z=-0.8077, loop=0/48)
	After any wing-joining, our area            is   14.80 m*m.
	After any wing-joining, our semi-length     is    6.05 m.
	After any wing-joining, our root chord      is   11.43 m.
	After any wing-joining, our tip chord       is    1.25 m.
	After any wing-joining, our mean aero sweep is   46.0 deg.
	After any wing-joining, our aspect ratio    is  2.3832.
	After any wing-joining, spanwise centroid   is  0.3385 semi-spans. (this is area centroid fraction of the way out to the tip)
	After any wing-joining, our taper ratio     is  0.0498.
	Oswalds efficiency is therefore  0.9591.

Finite-wing and build-up for Right Wing 2: Wing area for this wing is  9.6737 m*m.
	NOTE! I AM ADDING Right Wing 1 TO THE ROOT OF Right Wing 2 (through any intermediate wings) TO FORM ONE CONTINUOUS WING! (S=14.8001 m*m, connecting at x=1.1095, y=-0.0305, z=-0.8077, loop=0/48)
	After any wing-joining, our area            is   14.80 m*m.
	After any wing-joining, our semi-length     is    6.05 m.
	After any wing-joining, our root chord      is   11.43 m.
	After any wing-joining, our tip chord       is    1.25 m.
	After any wing-joining, our mean aero sweep is   46.0 deg.
	After any wing-joining, our aspect ratio    is  2.3832.
	After any wing-joining, spanwise centroid   is  0.3385 semi-spans. (this is area centroid fraction of the way out to the tip)
	After any wing-joining, our taper ratio     is  0.0498.
	Oswalds efficiency is therefore  0.9591.

Finite-wing and build-up for Right Wing 3: Wing area for this wing is  1.6686 m*m.
	NOTE! I AM ADDING Right Wing 1 TO THE ROOT OF Right Wing 3 (through any intermediate wings) TO FORM ONE CONTINUOUS WING! (S=6.7950 m*m, connecting at x=-1.0881, y=-0.0305, z=-1.7744, loop=0/48)
	After any wing-joining, our area            is    6.79 m*m.
	After any wing-joining, our semi-length     is    2.35 m.
	After any wing-joining, our root chord      is   11.43 m.
	After any wing-joining, our tip chord       is    4.05 m.
	After any wing-joining, our mean aero sweep is   68.4 deg.
	After any wing-joining, our aspect ratio    is  0.5000.
	After any wing-joining, spanwise centroid   is  0.4062 semi-spans. (this is area centroid fraction of the way out to the tip)
	After any wing-joining, our taper ratio     is  0.4484.
	Oswalds efficiency is therefore  1.0000.

Finite-wing and build-up for Right Wing 3: Wing area for this wing is  1.6686 m*m.
	NOTE! I AM ADDING Right Wing 1 TO THE ROOT OF Right Wing 3 (through any intermediate wings) TO FORM ONE CONTINUOUS WING! (S=6.7950 m*m, connecting at x=1.0881, y=-0.0305, z=-1.7744, loop=0/48)
	After any wing-joining, our area            is    6.79 m*m.
	After any wing-joining, our semi-length     is    2.35 m.
	After any wing-joining, our root chord      is   11.43 m.
	After any wing-joining, our tip chord       is    4.05 m.
	After any wing-joining, our mean aero sweep is   68.4 deg.
	After any wing-joining, our aspect ratio    is  0.5000.
	After any wing-joining, spanwise centroid   is  0.4062 semi-spans. (this is area centroid fraction of the way out to the tip)
	After any wing-joining, our taper ratio     is  0.4484.
	Oswalds efficiency is therefore  1.0000.

Finite-wing and build-up for Right Stab: Wing area for this wing is  3.0045 m*m.
	After any wing-joining, our area            is    3.00 m*m.
	After any wing-joining, our semi-length     is    2.12 m.
	After any wing-joining, our root chord      is    2.44 m.
	After any wing-joining, our tip chord       is    0.91 m.
	After any wing-joining, our mean aero sweep is   32.0 deg.
	After any wing-joining, our aspect ratio    is  2.1421.
	After any wing-joining, spanwise centroid   is  0.5000 semi-spans. (this is area centroid fraction of the way out to the tip)
	After any wing-joining, our taper ratio     is  1.0000.
	Oswalds efficiency is therefore  0.9901.

Finite-wing and build-up for Right Stab: Wing area for this wing is  3.0045 m*m.
	After any wing-joining, our area            is    3.00 m*m.
	After any wing-joining, our semi-length     is    2.12 m.
	After any wing-joining, our root chord      is    2.44 m.
	After any wing-joining, our tip chord       is    0.91 m.
	After any wing-joining, our mean aero sweep is   32.0 deg.
	After any wing-joining, our aspect ratio    is  2.1421.
	After any wing-joining, spanwise centroid   is  0.5000 semi-spans. (this is area centroid fraction of the way out to the tip)
	After any wing-joining, our taper ratio     is  1.0000.
	Oswalds efficiency is therefore  0.9901.

Finite-wing and build-up for Vert Stab 1: Wing area for this wing is  1.9777 m*m.
	After any wing-joining, our area            is    1.98 m*m.
	After any wing-joining, our semi-length     is    1.83 m.
	After any wing-joining, our root chord      is    5.03 m.
	After any wing-joining, our tip chord       is    2.96 m.
	After any wing-joining, our mean aero sweep is   74.1 deg.
	After any wing-joining, our aspect ratio    is  0.5000.
	After any wing-joining, spanwise centroid   is  0.4599 semi-spans. (this is area centroid fraction of the way out to the tip)
	After any wing-joining, our taper ratio     is  0.7640.
	Oswalds efficiency is therefore  1.0000.

Finite-wing and build-up for Vert Stab 2: Wing area for this wing is  3.8568 m*m.
	After any wing-joining, our area            is    3.86 m*m.
	After any wing-joining, our semi-length     is    2.90 m.
	After any wing-joining, our root chord      is    2.56 m.
	After any wing-joining, our tip chord       is    1.21 m.
	After any wing-joining, our mean aero sweep is   45.0 deg.
	After any wing-joining, our aspect ratio    is  2.1740.
	After any wing-joining, spanwise centroid   is  0.4439 semi-spans. (this is area centroid fraction of the way out to the tip)
	After any wing-joining, our taper ratio     is  0.6698.
	Oswalds efficiency is therefore  0.9991.



Engine # 0 is mass 1804.378 kg at x=   0.00, y=   0.03, z=   6.00 (for moment of inertia build-up)


Fuel tank # 0 is mass  31.291 kg at x=   0.00,  y=   0.34,  z=  -2.44 (for moment of inertia build-up)
Fuel tank # 1 is mass  31.291 kg at x=   0.00,  y=   0.34,  z=  -1.22 (for moment of inertia build-up)
Fuel tank # 2 is mass  10.662 kg at x=  -0.30,  y=   0.34,  z=   0.00 (for moment of inertia build-up)
Fuel tank # 3 is mass  10.662 kg at x=   0.30,  y=   0.34,  z=   0.00 (for moment of inertia build-up)
Fuel tank # 4 is mass  52.847 kg at x=   0.00,  y=   0.34,  z=   2.13 (for moment of inertia build-up)
Fuel tank # 5 is mass  12.748 kg at x=  -2.59,  y=   0.06,  z=   0.91 (for moment of inertia build-up)
Fuel tank # 6 is mass  12.748 kg at x=   2.59,  y=   0.06,  z=   0.91 (for moment of inertia build-up)
Fuel tank # 7 is mass  34.768 kg at x=  -0.61,  y=   0.49,  z=   0.00 (for moment of inertia build-up)
Fuel tank # 8 is mass  34.768 kg at x=   0.61,  y=   0.49,  z=   0.00 (for moment of inertia build-up)

Right Wing 1 Running wetted area  1.0765 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     0.85 m, based on mass-distribution across the shell of the craft with the 0.01 thickness wing giving a 0.10 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in pitch is    1.99 m, based on mass-distribution across the shell of the craft with the 0.01 thickness wing giving a 0.10 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in yaw is      2.16 m, based on mass-distribution across the shell of the craft with the 0.01 thickness wing giving a 0.10 weighting per square meter on this flying surface.

Right Wing 1 Running wetted area  2.1531 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     0.85 m, based on mass-distribution across the shell of the craft with the 0.01 thickness wing giving a 0.10 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in pitch is    1.99 m, based on mass-distribution across the shell of the craft with the 0.01 thickness wing giving a 0.10 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in yaw is      2.16 m, based on mass-distribution across the shell of the craft with the 0.01 thickness wing giving a 0.10 weighting per square meter on this flying surface.

Right Wing 2 Running wetted area  4.8617 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     2.24 m, based on mass-distribution across the shell of the craft with the 0.08 thickness wing giving a 0.14 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in pitch is    1.39 m, based on mass-distribution across the shell of the craft with the 0.08 thickness wing giving a 0.14 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in yaw is      2.63 m, based on mass-distribution across the shell of the craft with the 0.08 thickness wing giving a 0.14 weighting per square meter on this flying surface.

Right Wing 2 Running wetted area  7.5703 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     2.49 m, based on mass-distribution across the shell of the craft with the 0.08 thickness wing giving a 0.14 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in pitch is    1.17 m, based on mass-distribution across the shell of the craft with the 0.08 thickness wing giving a 0.14 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in yaw is      2.75 m, based on mass-distribution across the shell of the craft with the 0.08 thickness wing giving a 0.14 weighting per square meter on this flying surface.

Right Wing 3 Running wetted area  7.9374 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     2.45 m, based on mass-distribution across the shell of the craft with the 0.02 thickness wing giving a 0.11 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in pitch is    1.17 m, based on mass-distribution across the shell of the craft with the 0.02 thickness wing giving a 0.11 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in yaw is      2.72 m, based on mass-distribution across the shell of the craft with the 0.02 thickness wing giving a 0.11 weighting per square meter on this flying surface.

Right Wing 3 Running wetted area  8.3045 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     2.41 m, based on mass-distribution across the shell of the craft with the 0.02 thickness wing giving a 0.11 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in pitch is    1.16 m, based on mass-distribution across the shell of the craft with the 0.02 thickness wing giving a 0.11 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in yaw is      2.68 m, based on mass-distribution across the shell of the craft with the 0.02 thickness wing giving a 0.11 weighting per square meter on this flying surface.

Right Stab Running wetted area  9.1758 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     2.42 m, based on mass-distribution across the shell of the craft with the 0.09 thickness wing giving a 0.14 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in pitch is    1.86 m, based on mass-distribution across the shell of the craft with the 0.09 thickness wing giving a 0.14 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in yaw is      3.05 m, based on mass-distribution across the shell of the craft with the 0.09 thickness wing giving a 0.14 weighting per square meter on this flying surface.

Right Stab Running wetted area 10.0472 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     2.42 m, based on mass-distribution across the shell of the craft with the 0.09 thickness wing giving a 0.14 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in pitch is    2.28 m, based on mass-distribution across the shell of the craft with the 0.09 thickness wing giving a 0.14 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in yaw is      3.32 m, based on mass-distribution across the shell of the craft with the 0.09 thickness wing giving a 0.14 weighting per square meter on this flying surface.

Vert Stab 1 Running wetted area 10.5613 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     2.37 m, based on mass-distribution across the shell of the craft with the 0.06 thickness wing giving a 0.13 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in pitch is    2.30 m, based on mass-distribution across the shell of the craft with the 0.06 thickness wing giving a 0.13 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in yaw is      3.28 m, based on mass-distribution across the shell of the craft with the 0.06 thickness wing giving a 0.13 weighting per square meter on this flying surface.

Vert Stab 2 Running wetted area 11.5641 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     2.35 m, based on mass-distribution across the shell of the craft with the 0.06 thickness wing giving a 0.13 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in pitch is    2.59 m, based on mass-distribution across the shell of the craft with the 0.06 thickness wing giving a 0.13 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in yaw is      3.37 m, based on mass-distribution across the shell of the craft with the 0.06 thickness wing giving a 0.13 weighting per square meter on this flying surface.


Body 1 (fuselage):
	The frontal      area                          is  1.9058 m*m.
	The side         area                          is 16.9154 m*m.
	The top          area                          is 18.1698 m*m.
	The lateral      centroid                      is    0.00 m.
	The vertical     centroid                      is   -0.07 m.
	The longitudinal centroid for lift at   0 slip is    3.80 m.
	The longitudinal centroid for lift at 180 slip is   10.62 meters

	Running wetted area 66.7710 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     1.15 m, based on mass-distribution across the shell of the craft.
	Running radius of gyration of the shell in pitch is    3.49 m, based on mass-distribution across the shell of the craft.
	Running radius of gyration of the shell in yaw is      3.60 m, based on mass-distribution across the shell of the craft.

Body 2 (engine to body fairing):
	The frontal      area                          is  0.3585 m*m.
	The side         area                          is  1.1555 m*m.
	The top          area                          is  1.7207 m*m.
	The lateral      centroid                      is    0.00 m.
	The vertical     centroid                      is    0.07 m.
	The longitudinal centroid for lift at   0 slip is    0.96 m.
	The longitudinal centroid for lift at 180 slip is    2.58 meters

	Running wetted area 71.8301 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     1.13 m, based on mass-distribution across the shell of the craft.
	Running radius of gyration of the shell in pitch is    3.57 m, based on mass-distribution across the shell of the craft.
	Running radius of gyration of the shell in yaw is      3.66 m, based on mass-distribution across the shell of the craft.

Sum of all engines have mass of 1804.38 kg ( 21% of total):
	The radius of gyration of the engines in roll is     0.03 m, based on all engine masses and locations.
	The radius of gyration of the engines in pitch is    6.00 m, based on all engine masses and locations.
	The radius of gyration of the engines in yaw is      6.00 m, based on all engine masses and locations.

Sum of all tanks have mass of 231.79 kg (  3% of total):
	The radius of gyration of the tanks in roll is     1.00 m, based on all tank masses and locations.
	The radius of gyration of the tanks in pitch is    1.51 m, based on all tank masses and locations.
	The radius of gyration of the tanks in yaw is      1.73 m, based on all tank masses and locations.

Remainder of the craft has mass 6536.73 ( 76% of total):
	The radius of gyration of the shell in roll is     1.13 m, based on mass-distribution across the shell of the craft.
	The radius of gyration of the shell in pitch is    3.57 m, based on mass-distribution across the shell of the craft.
	The radius of gyration of the shell in yaw is      3.66 m, based on mass-distribution across the shell of the craft.

Final combined results:
	The radius of gyration in roll is     1.00 m. (that's moment of inertia 8613.310 kg*m*m).
	The radius of gyration in pitch is    4.17 m. (that's moment of inertia 148722.469 kg*m*m).
	The radius of gyration in yaw is      4.23 m. (that's moment of inertia 153480.609 kg*m*m).

Wing area           : 32.9373 m*m. (For wings 1 through 4 only, each times the cosine of its' dihedral! This does not include stabilizers or misc wings!)
Wing MAC            :    5.33 m.   (For wings 1 through 4 only! This does not include stabilizers or misc wings!)
Long-arm of 25% MAC :   -0.70 m.   (For wings 1 through 4 only! This does not include stabilizers or misc wings!)

••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••
X-Plane, by Austin Meyer
122010
Simulating Aircraft/Laminar Research/Grumman F-14 Tomcat/F-14D.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 and build-up for Right Wing 1: Wing area for this wing is 13.0052 m*m.
	NOTE! I AM ADDING Right Wing 2 TO THE TIP OF Right Wing 1 (through any intermediate wings) TO FORM ONE CONTINUOUS WING! (S=29.7445 m*m, connecting at x=-2.6762, y=0.5162, z=0.0229, loop=0/48)
	After any wing-joining, our area            is   29.74 m*m.
	After any wing-joining, our semi-length     is   10.42 m.
	After any wing-joining, our root chord      is    7.44 m.
	After any wing-joining, our tip chord       is    1.27 m.
	After any wing-joining, our mean aero sweep is   28.8 deg.
	After any wing-joining, our aspect ratio    is  5.6054.
	After any wing-joining, spanwise centroid   is  0.3524 semi-spans. (this is area centroid fraction of the way out to the tip)
	After any wing-joining, our taper ratio     is  0.1318.
	Oswalds efficiency is therefore  0.9705.

Finite-wing and build-up for Right Wing 1: Wing area for this wing is 13.0052 m*m.
	NOTE! I AM ADDING Right Wing 2 TO THE TIP OF Right Wing 1 (through any intermediate wings) TO FORM ONE CONTINUOUS WING! (S=29.7445 m*m, connecting at x=2.6762, y=0.5162, z=0.0229, loop=0/48)
	After any wing-joining, our area            is   29.74 m*m.
	After any wing-joining, our semi-length     is   10.42 m.
	After any wing-joining, our root chord      is    7.44 m.
	After any wing-joining, our tip chord       is    1.27 m.
	After any wing-joining, our mean aero sweep is   28.8 deg.
	After any wing-joining, our aspect ratio    is  5.6054.
	After any wing-joining, spanwise centroid   is  0.3524 semi-spans. (this is area centroid fraction of the way out to the tip)
	After any wing-joining, our taper ratio     is  0.1318.
	Oswalds efficiency is therefore  0.9705.

Finite-wing and build-up for Right Wing 2: Wing area for this wing is 16.7393 m*m.
	NOTE! I AM ADDING Right Wing 1 TO THE ROOT OF Right Wing 2 (through any intermediate wings) TO FORM ONE CONTINUOUS WING! (S=29.7445 m*m, connecting at x=-2.6761, y=0.5090, z=0.0030, loop=0/48)
	After any wing-joining, our area            is   29.74 m*m.
	After any wing-joining, our semi-length     is   10.42 m.
	After any wing-joining, our root chord      is    7.44 m.
	After any wing-joining, our tip chord       is    1.27 m.
	After any wing-joining, our mean aero sweep is   28.8 deg.
	After any wing-joining, our aspect ratio    is  5.6054.
	After any wing-joining, spanwise centroid   is  0.3524 semi-spans. (this is area centroid fraction of the way out to the tip)
	After any wing-joining, our taper ratio     is  0.1318.
	Oswalds efficiency is therefore  0.9705.

Finite-wing and build-up for Right Wing 2: Wing area for this wing is 16.7393 m*m.
	NOTE! I AM ADDING Right Wing 1 TO THE ROOT OF Right Wing 2 (through any intermediate wings) TO FORM ONE CONTINUOUS WING! (S=29.7445 m*m, connecting at x=2.6761, y=0.5090, z=0.0030, loop=0/48)
	After any wing-joining, our area            is   29.74 m*m.
	After any wing-joining, our semi-length     is   10.42 m.
	After any wing-joining, our root chord      is    7.44 m.
	After any wing-joining, our tip chord       is    1.27 m.
	After any wing-joining, our mean aero sweep is   28.8 deg.
	After any wing-joining, our aspect ratio    is  5.6054.
	After any wing-joining, spanwise centroid   is  0.3524 semi-spans. (this is area centroid fraction of the way out to the tip)
	After any wing-joining, our taper ratio     is  0.1318.
	Oswalds efficiency is therefore  0.9705.

Finite-wing and build-up for Right Stab: Wing area for this wing is  7.9238 m*m.
	After any wing-joining, our area            is    7.92 m*m.
	After any wing-joining, our semi-length     is    4.51 m.
	After any wing-joining, our root chord      is    3.90 m.
	After any wing-joining, our tip chord       is    1.07 m.
	After any wing-joining, our mean aero sweep is   45.0 deg.
	After any wing-joining, our aspect ratio    is  2.5681.
	After any wing-joining, spanwise centroid   is  0.4064 semi-spans. (this is area centroid fraction of the way out to the tip)
	After any wing-joining, our taper ratio     is  0.4494.
	Oswalds efficiency is therefore  1.0000.

Finite-wing and build-up for Right Stab: Wing area for this wing is  7.9238 m*m.
	After any wing-joining, our area            is    7.92 m*m.
	After any wing-joining, our semi-length     is    4.51 m.
	After any wing-joining, our root chord      is    3.90 m.
	After any wing-joining, our tip chord       is    1.07 m.
	After any wing-joining, our mean aero sweep is   45.0 deg.
	After any wing-joining, our aspect ratio    is  2.5681.
	After any wing-joining, spanwise centroid   is  0.4064 semi-spans. (this is area centroid fraction of the way out to the tip)
	After any wing-joining, our taper ratio     is  0.4494.
	Oswalds efficiency is therefore  1.0000.

Finite-wing and build-up for Vert Stab 1: Wing area for this wing is  5.6343 m*m.
	After any wing-joining, our area            is    5.63 m*m.
	After any wing-joining, our semi-length     is    3.44 m.
	After any wing-joining, our root chord      is    3.17 m.
	After any wing-joining, our tip chord       is    1.19 m.
	After any wing-joining, our mean aero sweep is   41.4 deg.
	After any wing-joining, our aspect ratio    is  2.3693.
	After any wing-joining, spanwise centroid   is  0.4254 semi-spans. (this is area centroid fraction of the way out to the tip)
	After any wing-joining, our taper ratio     is  0.5610.
	Oswalds efficiency is therefore  1.0000.

Finite-wing and build-up for Vert Stab 2: Wing area for this wing is  5.6343 m*m.
	After any wing-joining, our area            is    5.63 m*m.
	After any wing-joining, our semi-length     is    3.44 m.
	After any wing-joining, our root chord      is    3.17 m.
	After any wing-joining, our tip chord       is    1.19 m.
	After any wing-joining, our mean aero sweep is   41.4 deg.
	After any wing-joining, our aspect ratio    is  2.3693.
	After any wing-joining, spanwise centroid   is  0.4254 semi-spans. (this is area centroid fraction of the way out to the tip)
	After any wing-joining, our taper ratio     is  0.5610.
	Oswalds efficiency is therefore  1.0000.

Finite-wing and build-up for Wing 1: Wing area for this wing is  1.0255 m*m.
	After any wing-joining, our area            is    1.03 m*m.
	After any wing-joining, our semi-length     is    0.64 m.
	After any wing-joining, our root chord      is    3.11 m.
	After any wing-joining, our tip chord       is    0.15 m.
	After any wing-joining, our mean aero sweep is  -11.0 deg.
	After any wing-joining, our aspect ratio    is  0.7699.
	After any wing-joining, spanwise centroid   is  0.5000 semi-spans. (this is area centroid fraction of the way out to the tip)
	After any wing-joining, our taper ratio     is  1.0000.
	Oswalds efficiency is therefore  1.0000.

Finite-wing and build-up for Wing 2: Wing area for this wing is  1.0289 m*m.
	After any wing-joining, our area            is    1.03 m*m.
	After any wing-joining, our semi-length     is    0.64 m.
	After any wing-joining, our root chord      is    3.11 m.
	After any wing-joining, our tip chord       is    0.15 m.
	After any wing-joining, our mean aero sweep is  -10.0 deg.
	After any wing-joining, our aspect ratio    is  0.7724.
	After any wing-joining, spanwise centroid   is  0.5000 semi-spans. (this is area centroid fraction of the way out to the tip)
	After any wing-joining, our taper ratio     is  1.0000.
	Oswalds efficiency is therefore  1.0000.

Applying biplane interference factor to Oswalds Efficiency! Applying effect to Vert Stab 1 due to Vert Stab 2. Gap= 3.0559, stagger=0.0000. This takes e from  1.0000 to  0.8958.
Applying biplane interference factor to Oswalds Efficiency! Applying effect to Vert Stab 2 due to Vert Stab 1. Gap= 3.0559, stagger=0.0000. This takes e from  1.0000 to  0.8958.
Applying biplane interference factor to Oswalds Efficiency! Applying effect to Wing 1 due to Wing 2. Gap= 2.9261, stagger=0.0055. This takes e from  1.0000 to  0.8694.
Applying biplane interference factor to Oswalds Efficiency! Applying effect to Wing 2 due to Wing 1. Gap= 2.9261, stagger=0.0055. This takes e from  1.0000 to  0.8694.


Engine # 0 is mass 1748.106 kg at x=  -1.45, y=  -0.11, z=   7.19 (for moment of inertia build-up)
Engine # 1 is mass 1748.106 kg at x=   1.45, y=  -0.11, z=   7.19 (for moment of inertia build-up)


Fuel tank # 0 is mass  64.664 kg at x=   0.00,  y=   0.24,  z=  -1.37 (for moment of inertia build-up)
Fuel tank # 1 is mass  41.885 kg at x=   0.00,  y=   0.24,  z=  -0.67 (for moment of inertia build-up)
Fuel tank # 2 is mass  27.188 kg at x=  -0.30,  y=   0.27,  z=  -0.03 (for moment of inertia build-up)
Fuel tank # 3 is mass   6.981 kg at x=  -0.00,  y=   0.09,  z=  -0.03 (for moment of inertia build-up)
Fuel tank # 4 is mass  29.393 kg at x=   0.30,  y=   0.27,  z=  -0.03 (for moment of inertia build-up)
Fuel tank # 5 is mass   6.981 kg at x=   0.00,  y=   0.09,  z=  -0.03 (for moment of inertia build-up)
Fuel tank # 6 is mass  99.936 kg at x=  -0.00,  y=   0.24,  z=   1.68 (for moment of inertia build-up)
Fuel tank # 7 is mass  45.191 kg at x=   2.74,  y=   0.00,  z=   0.76 (for moment of inertia build-up)
Fuel tank # 8 is mass  45.191 kg at x=   2.74,  y=   0.00,  z=   0.76 (for moment of inertia build-up)

Right Wing 1 Running wetted area  3.1096 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     1.84 m, based on mass-distribution across the shell of the craft with the 0.04 thickness wing giving a 0.12 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in pitch is    2.66 m, based on mass-distribution across the shell of the craft with the 0.04 thickness wing giving a 0.12 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in yaw is      3.15 m, based on mass-distribution across the shell of the craft with the 0.04 thickness wing giving a 0.12 weighting per square meter on this flying surface.

Right Wing 1 Running wetted area  6.2192 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     1.84 m, based on mass-distribution across the shell of the craft with the 0.04 thickness wing giving a 0.12 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in pitch is    2.66 m, based on mass-distribution across the shell of the craft with the 0.04 thickness wing giving a 0.12 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in yaw is      3.15 m, based on mass-distribution across the shell of the craft with the 0.04 thickness wing giving a 0.12 weighting per square meter on this flying surface.

Right Wing 2 Running wetted area 10.5714 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     4.28 m, based on mass-distribution across the shell of the craft with the 0.06 thickness wing giving a 0.13 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in pitch is    2.16 m, based on mass-distribution across the shell of the craft with the 0.06 thickness wing giving a 0.13 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in yaw is      4.75 m, based on mass-distribution across the shell of the craft with the 0.06 thickness wing giving a 0.13 weighting per square meter on this flying surface.

Right Wing 2 Running wetted area 14.9237 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     4.96 m, based on mass-distribution across the shell of the craft with the 0.06 thickness wing giving a 0.13 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in pitch is    1.92 m, based on mass-distribution across the shell of the craft with the 0.06 thickness wing giving a 0.13 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in yaw is      5.28 m, based on mass-distribution across the shell of the craft with the 0.06 thickness wing giving a 0.13 weighting per square meter on this flying surface.

Right Stab Running wetted area 16.7711 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     4.80 m, based on mass-distribution across the shell of the craft with the 0.03 thickness wing giving a 0.12 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in pitch is    2.56 m, based on mass-distribution across the shell of the craft with the 0.03 thickness wing giving a 0.12 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in yaw is      5.41 m, based on mass-distribution across the shell of the craft with the 0.03 thickness wing giving a 0.12 weighting per square meter on this flying surface.

Right Stab Running wetted area 18.6185 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     4.68 m, based on mass-distribution across the shell of the craft with the 0.03 thickness wing giving a 0.12 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in pitch is    2.97 m, based on mass-distribution across the shell of the craft with the 0.03 thickness wing giving a 0.12 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in yaw is      5.52 m, based on mass-distribution across the shell of the craft with the 0.03 thickness wing giving a 0.12 weighting per square meter on this flying surface.

Vert Stab 1 Running wetted area 20.0834 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     4.55 m, based on mass-distribution across the shell of the craft with the 0.06 thickness wing giving a 0.13 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in pitch is    3.28 m, based on mass-distribution across the shell of the craft with the 0.06 thickness wing giving a 0.13 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in yaw is      5.54 m, based on mass-distribution across the shell of the craft with the 0.06 thickness wing giving a 0.13 weighting per square meter on this flying surface.

Vert Stab 2 Running wetted area 21.5483 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     4.44 m, based on mass-distribution across the shell of the craft with the 0.06 thickness wing giving a 0.13 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in pitch is    3.53 m, based on mass-distribution across the shell of the craft with the 0.06 thickness wing giving a 0.13 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in yaw is      5.56 m, based on mass-distribution across the shell of the craft with the 0.06 thickness wing giving a 0.13 weighting per square meter on this flying surface.

Wing 1 Running wetted area 21.8150 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     4.42 m, based on mass-distribution across the shell of the craft with the 0.06 thickness wing giving a 0.13 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in pitch is    3.52 m, based on mass-distribution across the shell of the craft with the 0.06 thickness wing giving a 0.13 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in yaw is      5.54 m, based on mass-distribution across the shell of the craft with the 0.06 thickness wing giving a 0.13 weighting per square meter on this flying surface.

Wing 2 Running wetted area 22.0825 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     4.40 m, based on mass-distribution across the shell of the craft with the 0.06 thickness wing giving a 0.13 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in pitch is    3.52 m, based on mass-distribution across the shell of the craft with the 0.06 thickness wing giving a 0.13 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in yaw is      5.52 m, based on mass-distribution across the shell of the craft with the 0.06 thickness wing giving a 0.13 weighting per square meter on this flying surface.


Body 1 (fuselage):
	The frontal      area                          is  2.4884 m*m.
	The side         area                          is 16.3110 m*m.
	The top          area                          is 16.5759 m*m.
	The lateral      centroid                      is    0.00 m.
	The vertical     centroid                      is    0.61 m.
	The longitudinal centroid for lift at   0 slip is    3.29 m.
	The longitudinal centroid for lift at 180 slip is    9.14 meters

	Running wetted area 76.3798 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     2.46 m, based on mass-distribution across the shell of the craft.
	Running radius of gyration of the shell in pitch is    5.12 m, based on mass-distribution across the shell of the craft.
	Running radius of gyration of the shell in yaw is      5.60 m, based on mass-distribution across the shell of the craft.

Body 2:
	The frontal      area                          is  2.0857 m*m.
	The side         area                          is  6.0806 m*m.
	The top          area                          is 40.7051 m*m.
	The lateral      centroid                      is    0.00 m.
	The vertical     centroid                      is   -0.07 m.
	The longitudinal centroid for lift at   0 slip is    3.08 m.
	The longitudinal centroid for lift at 180 slip is    8.81 meters

	Running wetted area 168.2935 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     1.86 m, based on mass-distribution across the shell of the craft.
	Running radius of gyration of the shell in pitch is    4.19 m, based on mass-distribution across the shell of the craft.
	Running radius of gyration of the shell in yaw is      4.53 m, based on mass-distribution across the shell of the craft.

Body 22 (inlet left):
	The frontal      area                          is  1.9645 m*m.
	The side         area                          is 15.1585 m*m.
	The top          area                          is 17.8492 m*m.
	The lateral      centroid                      is    0.00 m.
	The vertical     centroid                      is   -0.02 m.
	The longitudinal centroid for lift at   0 slip is   -8.94 m.
	The longitudinal centroid for lift at 180 slip is   -2.87 meters

	Running wetted area 233.1992 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     1.70 m, based on mass-distribution across the shell of the craft.
	Running radius of gyration of the shell in pitch is    4.00 m, based on mass-distribution across the shell of the craft.
	Running radius of gyration of the shell in yaw is      4.29 m, based on mass-distribution across the shell of the craft.

Body 23 (inlet right):
	The frontal      area                          is  1.9645 m*m.
	The side         area                          is 15.1585 m*m.
	The top          area                          is 17.8492 m*m.
	The lateral      centroid                      is    0.00 m.
	The vertical     centroid                      is   -0.02 m.
	The longitudinal centroid for lift at   0 slip is   -8.94 m.
	The longitudinal centroid for lift at 180 slip is   -2.87 meters

	Running wetted area 298.1046 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     1.75 m, based on mass-distribution across the shell of the craft.
	Running radius of gyration of the shell in pitch is    3.89 m, based on mass-distribution across the shell of the craft.
	Running radius of gyration of the shell in yaw is      4.20 m, based on mass-distribution across the shell of the craft.

Sum of all engines have mass of 3496.21 kg ( 18% of total):
	The radius of gyration of the engines in roll is     1.46 m, based on all engine masses and locations.
	The radius of gyration of the engines in pitch is    7.19 m, based on all engine masses and locations.
	The radius of gyration of the engines in yaw is      7.34 m, based on all engine masses and locations.

Sum of all tanks have mass of 367.41 kg (  2% of total):
	The radius of gyration of the tanks in roll is     1.38 m, based on all tank masses and locations.
	The radius of gyration of the tanks in pitch is    1.16 m, based on all tank masses and locations.
	The radius of gyration of the tanks in yaw is      1.78 m, based on all tank masses and locations.

Remainder of the craft has mass 15087.47 ( 80% of total):
	The radius of gyration of the shell in roll is     1.75 m, based on mass-distribution across the shell of the craft.
	The radius of gyration of the shell in pitch is    3.89 m, based on mass-distribution across the shell of the craft.
	The radius of gyration of the shell in yaw is      4.20 m, based on mass-distribution across the shell of the craft.

Final combined results:
	The radius of gyration in roll is     1.69 m. (that's moment of inertia 54364.344 kg*m*m).
	The radius of gyration in pitch is    4.65 m. (that's moment of inertia 409755.188 kg*m*m).
	The radius of gyration in yaw is      4.91 m. (that's moment of inertia 456187.625 kg*m*m).

Wing area           : 59.4646 m*m. (For wings 1 through 4 only, each times the cosine of its' dihedral! This does not include stabilizers or misc wings!)
Wing MAC            :    4.39 m.   (For wings 1 through 4 only! This does not include stabilizers or misc wings!)
Long-arm of 25% MAC :   -0.66 m.   (For wings 1 through 4 only! This does not include stabilizers or misc wings!)

••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••
X-Plane, by Austin Meyer
122010
Simulating Aircraft/Laminar Research/Grumman F-14 Tomcat/F-14D.acf
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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 and build-up for Right Wing 1: Wing area for this wing is 13.0052 m*m.
	NOTE! I AM ADDING Right Wing 2 TO THE TIP OF Right Wing 1 (through any intermediate wings) TO FORM ONE CONTINUOUS WING! (S=29.7445 m*m, connecting at x=-2.6762, y=0.5162, z=0.0229, loop=0/48)
	After any wing-joining, our area            is   29.74 m*m.
	After any wing-joining, our semi-length     is   10.42 m.
	After any wing-joining, our root chord      is    7.44 m.
	After any wing-joining, our tip chord       is    1.27 m.
	After any wing-joining, our mean aero sweep is   28.8 deg.
	After any wing-joining, our aspect ratio    is  5.6054.
	After any wing-joining, spanwise centroid   is  0.3524 semi-spans. (this is area centroid fraction of the way out to the tip)
	After any wing-joining, our taper ratio     is  0.1318.
	Oswalds efficiency is therefore  0.9705.

Finite-wing and build-up for Right Wing 1: Wing area for this wing is 13.0052 m*m.
	NOTE! I AM ADDING Right Wing 2 TO THE TIP OF Right Wing 1 (through any intermediate wings) TO FORM ONE CONTINUOUS WING! (S=29.7445 m*m, connecting at x=2.6762, y=0.5162, z=0.0229, loop=0/48)
	After any wing-joining, our area            is   29.74 m*m.
	After any wing-joining, our semi-length     is   10.42 m.
	After any wing-joining, our root chord      is    7.44 m.
	After any wing-joining, our tip chord       is    1.27 m.
	After any wing-joining, our mean aero sweep is   28.8 deg.
	After any wing-joining, our aspect ratio    is  5.6054.
	After any wing-joining, spanwise centroid   is  0.3524 semi-spans. (this is area centroid fraction of the way out to the tip)
	After any wing-joining, our taper ratio     is  0.1318.
	Oswalds efficiency is therefore  0.9705.

Finite-wing and build-up for Right Wing 2: Wing area for this wing is 16.7393 m*m.
	NOTE! I AM ADDING Right Wing 1 TO THE ROOT OF Right Wing 2 (through any intermediate wings) TO FORM ONE CONTINUOUS WING! (S=29.7445 m*m, connecting at x=-2.6761, y=0.5090, z=0.0030, loop=0/48)
	After any wing-joining, our area            is   29.74 m*m.
	After any wing-joining, our semi-length     is   10.42 m.
	After any wing-joining, our root chord      is    7.44 m.
	After any wing-joining, our tip chord       is    1.27 m.
	After any wing-joining, our mean aero sweep is   28.8 deg.
	After any wing-joining, our aspect ratio    is  5.6054.
	After any wing-joining, spanwise centroid   is  0.3524 semi-spans. (this is area centroid fraction of the way out to the tip)
	After any wing-joining, our taper ratio     is  0.1318.
	Oswalds efficiency is therefore  0.9705.

Finite-wing and build-up for Right Wing 2: Wing area for this wing is 16.7393 m*m.
	NOTE! I AM ADDING Right Wing 1 TO THE ROOT OF Right Wing 2 (through any intermediate wings) TO FORM ONE CONTINUOUS WING! (S=29.7445 m*m, connecting at x=2.6761, y=0.5090, z=0.0030, loop=0/48)
	After any wing-joining, our area            is   29.74 m*m.
	After any wing-joining, our semi-length     is   10.42 m.
	After any wing-joining, our root chord      is    7.44 m.
	After any wing-joining, our tip chord       is    1.27 m.
	After any wing-joining, our mean aero sweep is   28.8 deg.
	After any wing-joining, our aspect ratio    is  5.6054.
	After any wing-joining, spanwise centroid   is  0.3524 semi-spans. (this is area centroid fraction of the way out to the tip)
	After any wing-joining, our taper ratio     is  0.1318.
	Oswalds efficiency is therefore  0.9705.

Finite-wing and build-up for Right Stab: Wing area for this wing is  7.9238 m*m.
	After any wing-joining, our area            is    7.92 m*m.
	After any wing-joining, our semi-length     is    4.51 m.
	After any wing-joining, our root chord      is    3.90 m.
	After any wing-joining, our tip chord       is    1.07 m.
	After any wing-joining, our mean aero sweep is   45.0 deg.
	After any wing-joining, our aspect ratio    is  2.5681.
	After any wing-joining, spanwise centroid   is  0.4064 semi-spans. (this is area centroid fraction of the way out to the tip)
	After any wing-joining, our taper ratio     is  0.4494.
	Oswalds efficiency is therefore  1.0000.

Finite-wing and build-up for Right Stab: Wing area for this wing is  7.9238 m*m.
	After any wing-joining, our area            is    7.92 m*m.
	After any wing-joining, our semi-length     is    4.51 m.
	After any wing-joining, our root chord      is    3.90 m.
	After any wing-joining, our tip chord       is    1.07 m.
	After any wing-joining, our mean aero sweep is   45.0 deg.
	After any wing-joining, our aspect ratio    is  2.5681.
	After any wing-joining, spanwise centroid   is  0.4064 semi-spans. (this is area centroid fraction of the way out to the tip)
	After any wing-joining, our taper ratio     is  0.4494.
	Oswalds efficiency is therefore  1.0000.

Finite-wing and build-up for Vert Stab 1: Wing area for this wing is  5.6343 m*m.
	After any wing-joining, our area            is    5.63 m*m.
	After any wing-joining, our semi-length     is    3.44 m.
	After any wing-joining, our root chord      is    3.17 m.
	After any wing-joining, our tip chord       is    1.19 m.
	After any wing-joining, our mean aero sweep is   41.4 deg.
	After any wing-joining, our aspect ratio    is  2.3693.
	After any wing-joining, spanwise centroid   is  0.4254 semi-spans. (this is area centroid fraction of the way out to the tip)
	After any wing-joining, our taper ratio     is  0.5610.
	Oswalds efficiency is therefore  1.0000.

Finite-wing and build-up for Vert Stab 2: Wing area for this wing is  5.6343 m*m.
	After any wing-joining, our area            is    5.63 m*m.
	After any wing-joining, our semi-length     is    3.44 m.
	After any wing-joining, our root chord      is    3.17 m.
	After any wing-joining, our tip chord       is    1.19 m.
	After any wing-joining, our mean aero sweep is   41.4 deg.
	After any wing-joining, our aspect ratio    is  2.3693.
	After any wing-joining, spanwise centroid   is  0.4254 semi-spans. (this is area centroid fraction of the way out to the tip)
	After any wing-joining, our taper ratio     is  0.5610.
	Oswalds efficiency is therefore  1.0000.

Finite-wing and build-up for Wing 1: Wing area for this wing is  1.0255 m*m.
	After any wing-joining, our area            is    1.03 m*m.
	After any wing-joining, our semi-length     is    0.64 m.
	After any wing-joining, our root chord      is    3.11 m.
	After any wing-joining, our tip chord       is    0.15 m.
	After any wing-joining, our mean aero sweep is  -11.0 deg.
	After any wing-joining, our aspect ratio    is  0.7699.
	After any wing-joining, spanwise centroid   is  0.5000 semi-spans. (this is area centroid fraction of the way out to the tip)
	After any wing-joining, our taper ratio     is  1.0000.
	Oswalds efficiency is therefore  1.0000.

Finite-wing and build-up for Wing 2: Wing area for this wing is  1.0289 m*m.
	After any wing-joining, our area            is    1.03 m*m.
	After any wing-joining, our semi-length     is    0.64 m.
	After any wing-joining, our root chord      is    3.11 m.
	After any wing-joining, our tip chord       is    0.15 m.
	After any wing-joining, our mean aero sweep is  -10.0 deg.
	After any wing-joining, our aspect ratio    is  0.7724.
	After any wing-joining, spanwise centroid   is  0.5000 semi-spans. (this is area centroid fraction of the way out to the tip)
	After any wing-joining, our taper ratio     is  1.0000.
	Oswalds efficiency is therefore  1.0000.

Applying biplane interference factor to Oswalds Efficiency! Applying effect to Vert Stab 1 due to Vert Stab 2. Gap= 3.0559, stagger=0.0000. This takes e from  1.0000 to  0.8958.
Applying biplane interference factor to Oswalds Efficiency! Applying effect to Vert Stab 2 due to Vert Stab 1. Gap= 3.0559, stagger=0.0000. This takes e from  1.0000 to  0.8958.
Applying biplane interference factor to Oswalds Efficiency! Applying effect to Wing 1 due to Wing 2. Gap= 2.9261, stagger=0.0055. This takes e from  1.0000 to  0.8694.
Applying biplane interference factor to Oswalds Efficiency! Applying effect to Wing 2 due to Wing 1. Gap= 2.9261, stagger=0.0055. This takes e from  1.0000 to  0.8694.


Engine # 0 is mass 1748.106 kg at x=  -1.45, y=  -0.11, z=   7.19 (for moment of inertia build-up)
Engine # 1 is mass 1748.106 kg at x=   1.45, y=  -0.11, z=   7.19 (for moment of inertia build-up)


Fuel tank # 0 is mass  64.664 kg at x=   0.00,  y=   0.24,  z=  -1.37 (for moment of inertia build-up)
Fuel tank # 1 is mass  41.885 kg at x=   0.00,  y=   0.24,  z=  -0.67 (for moment of inertia build-up)
Fuel tank # 2 is mass  27.188 kg at x=  -0.30,  y=   0.27,  z=  -0.03 (for moment of inertia build-up)
Fuel tank # 3 is mass   6.981 kg at x=  -0.00,  y=   0.09,  z=  -0.03 (for moment of inertia build-up)
Fuel tank # 4 is mass  29.393 kg at x=   0.30,  y=   0.27,  z=  -0.03 (for moment of inertia build-up)
Fuel tank # 5 is mass   6.981 kg at x=   0.00,  y=   0.09,  z=  -0.03 (for moment of inertia build-up)
Fuel tank # 6 is mass  99.936 kg at x=  -0.00,  y=   0.24,  z=   1.68 (for moment of inertia build-up)
Fuel tank # 7 is mass  45.191 kg at x=   2.74,  y=   0.00,  z=   0.76 (for moment of inertia build-up)
Fuel tank # 8 is mass  45.191 kg at x=   2.74,  y=   0.00,  z=   0.76 (for moment of inertia build-up)

Right Wing 1 Running wetted area  3.1096 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     1.84 m, based on mass-distribution across the shell of the craft with the 0.04 thickness wing giving a 0.12 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in pitch is    2.66 m, based on mass-distribution across the shell of the craft with the 0.04 thickness wing giving a 0.12 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in yaw is      3.15 m, based on mass-distribution across the shell of the craft with the 0.04 thickness wing giving a 0.12 weighting per square meter on this flying surface.

Right Wing 1 Running wetted area  6.2192 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     1.84 m, based on mass-distribution across the shell of the craft with the 0.04 thickness wing giving a 0.12 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in pitch is    2.66 m, based on mass-distribution across the shell of the craft with the 0.04 thickness wing giving a 0.12 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in yaw is      3.15 m, based on mass-distribution across the shell of the craft with the 0.04 thickness wing giving a 0.12 weighting per square meter on this flying surface.

Right Wing 2 Running wetted area 10.5714 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     4.28 m, based on mass-distribution across the shell of the craft with the 0.06 thickness wing giving a 0.13 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in pitch is    2.16 m, based on mass-distribution across the shell of the craft with the 0.06 thickness wing giving a 0.13 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in yaw is      4.75 m, based on mass-distribution across the shell of the craft with the 0.06 thickness wing giving a 0.13 weighting per square meter on this flying surface.

Right Wing 2 Running wetted area 14.9237 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     4.96 m, based on mass-distribution across the shell of the craft with the 0.06 thickness wing giving a 0.13 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in pitch is    1.92 m, based on mass-distribution across the shell of the craft with the 0.06 thickness wing giving a 0.13 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in yaw is      5.28 m, based on mass-distribution across the shell of the craft with the 0.06 thickness wing giving a 0.13 weighting per square meter on this flying surface.

Right Stab Running wetted area 16.7711 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     4.80 m, based on mass-distribution across the shell of the craft with the 0.03 thickness wing giving a 0.12 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in pitch is    2.56 m, based on mass-distribution across the shell of the craft with the 0.03 thickness wing giving a 0.12 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in yaw is      5.41 m, based on mass-distribution across the shell of the craft with the 0.03 thickness wing giving a 0.12 weighting per square meter on this flying surface.

Right Stab Running wetted area 18.6185 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     4.68 m, based on mass-distribution across the shell of the craft with the 0.03 thickness wing giving a 0.12 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in pitch is    2.97 m, based on mass-distribution across the shell of the craft with the 0.03 thickness wing giving a 0.12 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in yaw is      5.52 m, based on mass-distribution across the shell of the craft with the 0.03 thickness wing giving a 0.12 weighting per square meter on this flying surface.

Vert Stab 1 Running wetted area 20.0834 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     4.55 m, based on mass-distribution across the shell of the craft with the 0.06 thickness wing giving a 0.13 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in pitch is    3.28 m, based on mass-distribution across the shell of the craft with the 0.06 thickness wing giving a 0.13 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in yaw is      5.54 m, based on mass-distribution across the shell of the craft with the 0.06 thickness wing giving a 0.13 weighting per square meter on this flying surface.

Vert Stab 2 Running wetted area 21.5483 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     4.44 m, based on mass-distribution across the shell of the craft with the 0.06 thickness wing giving a 0.13 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in pitch is    3.53 m, based on mass-distribution across the shell of the craft with the 0.06 thickness wing giving a 0.13 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in yaw is      5.56 m, based on mass-distribution across the shell of the craft with the 0.06 thickness wing giving a 0.13 weighting per square meter on this flying surface.

Wing 1 Running wetted area 21.8150 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     4.42 m, based on mass-distribution across the shell of the craft with the 0.06 thickness wing giving a 0.13 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in pitch is    3.52 m, based on mass-distribution across the shell of the craft with the 0.06 thickness wing giving a 0.13 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in yaw is      5.54 m, based on mass-distribution across the shell of the craft with the 0.06 thickness wing giving a 0.13 weighting per square meter on this flying surface.

Wing 2 Running wetted area 22.0825 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     4.40 m, based on mass-distribution across the shell of the craft with the 0.06 thickness wing giving a 0.13 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in pitch is    3.52 m, based on mass-distribution across the shell of the craft with the 0.06 thickness wing giving a 0.13 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in yaw is      5.52 m, based on mass-distribution across the shell of the craft with the 0.06 thickness wing giving a 0.13 weighting per square meter on this flying surface.


Body 1 (fuselage):
	The frontal      area                          is  2.4884 m*m.
	The side         area                          is 16.3110 m*m.
	The top          area                          is 16.5759 m*m.
	The lateral      centroid                      is    0.00 m.
	The vertical     centroid                      is    0.61 m.
	The longitudinal centroid for lift at   0 slip is    3.29 m.
	The longitudinal centroid for lift at 180 slip is    9.14 meters

	Running wetted area 76.3798 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     2.46 m, based on mass-distribution across the shell of the craft.
	Running radius of gyration of the shell in pitch is    5.12 m, based on mass-distribution across the shell of the craft.
	Running radius of gyration of the shell in yaw is      5.60 m, based on mass-distribution across the shell of the craft.

Body 2:
	The frontal      area                          is  2.0857 m*m.
	The side         area                          is  6.0806 m*m.
	The top          area                          is 40.7051 m*m.
	The lateral      centroid                      is    0.00 m.
	The vertical     centroid                      is   -0.07 m.
	The longitudinal centroid for lift at   0 slip is    3.08 m.
	The longitudinal centroid for lift at 180 slip is    8.81 meters

	Running wetted area 168.2935 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     1.86 m, based on mass-distribution across the shell of the craft.
	Running radius of gyration of the shell in pitch is    4.19 m, based on mass-distribution across the shell of the craft.
	Running radius of gyration of the shell in yaw is      4.53 m, based on mass-distribution across the shell of the craft.

Body 22 (inlet left):
	The frontal      area                          is  1.9645 m*m.
	The side         area                          is 15.1585 m*m.
	The top          area                          is 17.8492 m*m.
	The lateral      centroid                      is    0.00 m.
	The vertical     centroid                      is   -0.02 m.
	The longitudinal centroid for lift at   0 slip is   -8.94 m.
	The longitudinal centroid for lift at 180 slip is   -2.87 meters

	Running wetted area 233.1992 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     1.70 m, based on mass-distribution across the shell of the craft.
	Running radius of gyration of the shell in pitch is    4.00 m, based on mass-distribution across the shell of the craft.
	Running radius of gyration of the shell in yaw is      4.29 m, based on mass-distribution across the shell of the craft.

Body 23 (inlet right):
	The frontal      area                          is  1.9645 m*m.
	The side         area                          is 15.1585 m*m.
	The top          area                          is 17.8492 m*m.
	The lateral      centroid                      is    0.00 m.
	The vertical     centroid                      is   -0.02 m.
	The longitudinal centroid for lift at   0 slip is   -8.94 m.
	The longitudinal centroid for lift at 180 slip is   -2.87 meters

	Running wetted area 298.1046 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     1.75 m, based on mass-distribution across the shell of the craft.
	Running radius of gyration of the shell in pitch is    3.89 m, based on mass-distribution across the shell of the craft.
	Running radius of gyration of the shell in yaw is      4.20 m, based on mass-distribution across the shell of the craft.

Sum of all engines have mass of 3496.21 kg ( 18% of total):
	The radius of gyration of the engines in roll is     1.46 m, based on all engine masses and locations.
	The radius of gyration of the engines in pitch is    7.19 m, based on all engine masses and locations.
	The radius of gyration of the engines in yaw is      7.34 m, based on all engine masses and locations.

Sum of all tanks have mass of 367.41 kg (  2% of total):
	The radius of gyration of the tanks in roll is     1.38 m, based on all tank masses and locations.
	The radius of gyration of the tanks in pitch is    1.16 m, based on all tank masses and locations.
	The radius of gyration of the tanks in yaw is      1.78 m, based on all tank masses and locations.

Remainder of the craft has mass 15087.47 ( 80% of total):
	The radius of gyration of the shell in roll is     1.75 m, based on mass-distribution across the shell of the craft.
	The radius of gyration of the shell in pitch is    3.89 m, based on mass-distribution across the shell of the craft.
	The radius of gyration of the shell in yaw is      4.20 m, based on mass-distribution across the shell of the craft.

Final combined results:
	The radius of gyration in roll is     1.69 m. (that's moment of inertia 54364.344 kg*m*m).
	The radius of gyration in pitch is    4.65 m. (that's moment of inertia 409755.188 kg*m*m).
	The radius of gyration in yaw is      4.91 m. (that's moment of inertia 456187.625 kg*m*m).

Wing area           : 59.4646 m*m. (For wings 1 through 4 only, each times the cosine of its' dihedral! This does not include stabilizers or misc wings!)
Wing MAC            :    4.39 m.   (For wings 1 through 4 only! This does not include stabilizers or misc wings!)
Long-arm of 25% MAC :   -0.66 m.   (For wings 1 through 4 only! This does not include stabilizers or misc wings!)

