••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••
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/McDonnell Douglas F-4 Phantom II/F-4.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 20.1316 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=24.4180 m*m, connecting at x=-3.9872, y=-0.6066, z=1.3172, loop=0/48)
	After any wing-joining, our area            is   24.42 m*m.
	After any wing-joining, our semi-length     is    8.10 m.
	After any wing-joining, our root chord      is    7.17 m.
	After any wing-joining, our tip chord       is    1.31 m.
	After any wing-joining, our mean aero sweep is   43.9 deg.
	After any wing-joining, our aspect ratio    is  2.7920.
	After any wing-joining, spanwise centroid   is  0.3865 semi-spans. (this is area centroid fraction of the way out to the tip)
	After any wing-joining, our taper ratio     is  0.3326.
	Oswalds efficiency is therefore  1.0000.

Finite-wing and build-up for Right Wing 1: Wing area for this wing is 20.1316 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=24.4180 m*m, connecting at x=3.9872, y=-0.6066, z=1.3172, loop=0/48)
	After any wing-joining, our area            is   24.42 m*m.
	After any wing-joining, our semi-length     is    8.10 m.
	After any wing-joining, our root chord      is    7.17 m.
	After any wing-joining, our tip chord       is    1.31 m.
	After any wing-joining, our mean aero sweep is   43.9 deg.
	After any wing-joining, our aspect ratio    is  2.7920.
	After any wing-joining, spanwise centroid   is  0.3865 semi-spans. (this is area centroid fraction of the way out to the tip)
	After any wing-joining, our taper ratio     is  0.3326.
	Oswalds efficiency is therefore  1.0000.

Finite-wing and build-up for Right Wing 2: Wing area for this wing is  4.2864 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=24.4180 m*m, connecting at x=-3.9898, y=-0.5852, z=1.0638, loop=0/48)
	After any wing-joining, our area            is   24.42 m*m.
	After any wing-joining, our semi-length     is    8.10 m.
	After any wing-joining, our root chord      is    7.17 m.
	After any wing-joining, our tip chord       is    1.31 m.
	After any wing-joining, our mean aero sweep is   43.9 deg.
	After any wing-joining, our aspect ratio    is  2.7920.
	After any wing-joining, spanwise centroid   is  0.3865 semi-spans. (this is area centroid fraction of the way out to the tip)
	After any wing-joining, our taper ratio     is  0.3326.
	Oswalds efficiency is therefore  1.0000.

Finite-wing and build-up for Right Wing 2: Wing area for this wing is  4.2864 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=24.4180 m*m, connecting at x=3.9898, y=-0.5852, z=1.0638, loop=0/48)
	After any wing-joining, our area            is   24.42 m*m.
	After any wing-joining, our semi-length     is    8.10 m.
	After any wing-joining, our root chord      is    7.17 m.
	After any wing-joining, our tip chord       is    1.31 m.
	After any wing-joining, our mean aero sweep is   43.9 deg.
	After any wing-joining, our aspect ratio    is  2.7920.
	After any wing-joining, spanwise centroid   is  0.3865 semi-spans. (this is area centroid fraction of the way out to the tip)
	After any wing-joining, our taper ratio     is  0.3326.
	Oswalds efficiency is therefore  1.0000.

Finite-wing and build-up for Right Wing 4: Wing area for this wing is  0.7241 m*m.
	After any wing-joining, our area            is    0.72 m*m.
	After any wing-joining, our semi-length     is    0.61 m.
	After any wing-joining, our root chord      is    1.52 m.
	After any wing-joining, our tip chord       is    1.22 m.
	After any wing-joining, our mean aero sweep is   30.0 deg.
	After any wing-joining, our aspect ratio    is  0.7698.
	After any wing-joining, spanwise centroid   is  0.4826 semi-spans. (this is area centroid fraction of the way out to the tip)
	After any wing-joining, our taper ratio     is  0.8979.
	Oswalds efficiency is therefore  1.0000.

Finite-wing and build-up for Right Wing 4: Wing area for this wing is  0.7241 m*m.
	After any wing-joining, our area            is    0.72 m*m.
	After any wing-joining, our semi-length     is    0.61 m.
	After any wing-joining, our root chord      is    1.52 m.
	After any wing-joining, our tip chord       is    1.22 m.
	After any wing-joining, our mean aero sweep is   30.0 deg.
	After any wing-joining, our aspect ratio    is  0.7698.
	After any wing-joining, spanwise centroid   is  0.4826 semi-spans. (this is area centroid fraction of the way out to the tip)
	After any wing-joining, our taper ratio     is  0.8979.
	Oswalds efficiency is therefore  1.0000.

Finite-wing and build-up for Right Stab: Wing area for this wing is  4.0084 m*m.
	After any wing-joining, our area            is    4.01 m*m.
	After any wing-joining, our semi-length     is    3.18 m.
	After any wing-joining, our root chord      is    2.44 m.
	After any wing-joining, our tip chord       is    0.64 m.
	After any wing-joining, our mean aero sweep is   35.0 deg.
	After any wing-joining, our aspect ratio    is  3.3837.
	After any wing-joining, spanwise centroid   is  0.4087 semi-spans. (this is area centroid fraction of the way out to the tip)
	After any wing-joining, our taper ratio     is  0.4631.
	Oswalds efficiency is therefore  1.0000.

Finite-wing and build-up for Right Stab: Wing area for this wing is  4.0084 m*m.
	After any wing-joining, our area            is    4.01 m*m.
	After any wing-joining, our semi-length     is    3.18 m.
	After any wing-joining, our root chord      is    2.44 m.
	After any wing-joining, our tip chord       is    0.64 m.
	After any wing-joining, our mean aero sweep is   35.0 deg.
	After any wing-joining, our aspect ratio    is  3.3837.
	After any wing-joining, spanwise centroid   is  0.4087 semi-spans. (this is area centroid fraction of the way out to the tip)
	After any wing-joining, our taper ratio     is  0.4631.
	Oswalds efficiency is therefore  1.0000.

Finite-wing and build-up for Vert Stab 1: Wing area for this wing is  6.3815 m*m.
	After any wing-joining, our area            is    6.38 m*m.
	After any wing-joining, our semi-length     is    3.90 m.
	After any wing-joining, our root chord      is    5.36 m.
	After any wing-joining, our tip chord       is    0.91 m.
	After any wing-joining, our mean aero sweep is   58.6 deg.
	After any wing-joining, our aspect ratio    is  1.2949.
	After any wing-joining, spanwise centroid   is  0.3843 semi-spans. (this is area centroid fraction of the way out to the tip)
	After any wing-joining, our taper ratio     is  0.3193.
	Oswalds efficiency is therefore  1.0000.

Applying biplane interference factor to Oswalds Efficiency! Applying effect to Right Wing 4 due to Right Wing 4. Gap= 4.2672, stagger=0.0000. This takes e from  1.0000 to  0.9503.
Applying biplane interference factor to Oswalds Efficiency! Applying effect to Right Wing 4 due to Right Wing 4. Gap= 4.2672, stagger=0.0000. This takes e from  1.0000 to  0.9503.


Engine # 0 is mass 1582.131 kg at x=  -0.59, y=  -0.43, z=   4.69 (for moment of inertia build-up)
Engine # 1 is mass 1582.131 kg at x=   0.59, y=  -0.43, z=   4.69 (for moment of inertia build-up)


Fuel tank # 0 is mass  34.029 kg at x=   0.00,  y=   0.30,  z=  -2.29 (for moment of inertia build-up)
Fuel tank # 1 is mass  34.029 kg at x=   0.00,  y=   0.46,  z=  -1.07 (for moment of inertia build-up)
Fuel tank # 2 is mass  34.029 kg at x=   0.00,  y=   0.46,  z=   0.46 (for moment of inertia build-up)
Fuel tank # 3 is mass  34.029 kg at x=   0.00,  y=   0.46,  z=   1.68 (for moment of inertia build-up)
Fuel tank # 4 is mass  34.029 kg at x=   0.00,  y=   0.46,  z=   2.74 (for moment of inertia build-up)
Fuel tank # 5 is mass  34.029 kg at x=   0.00,  y=   0.46,  z=   3.51 (for moment of inertia build-up)
Fuel tank # 6 is mass  52.590 kg at x=  -1.83,  y=  -0.58,  z=  -0.15 (for moment of inertia build-up)
Fuel tank # 7 is mass  52.590 kg at x=   1.83,  y=  -0.58,  z=  -0.15 (for moment of inertia build-up)

Right Wing 1 Running wetted area  5.0831 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     2.20 m, based on mass-distribution across the shell of the craft with the 0.05 thickness wing giving a 0.13 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in pitch is    1.53 m, based on mass-distribution across the shell of the craft with the 0.05 thickness wing giving a 0.13 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in yaw is      2.54 m, based on mass-distribution across the shell of the craft with the 0.05 thickness wing giving a 0.13 weighting per square meter on this flying surface.

Right Wing 1 Running wetted area 10.1663 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     2.20 m, based on mass-distribution across the shell of the craft with the 0.05 thickness wing giving a 0.13 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in pitch is    1.53 m, based on mass-distribution across the shell of the craft with the 0.05 thickness wing giving a 0.13 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in yaw is      2.54 m, based on mass-distribution across the shell of the craft with the 0.05 thickness wing giving a 0.13 weighting per square meter on this flying surface.

Right Wing 2 Running wetted area 11.1818 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     2.57 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    1.59 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      2.91 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 12.1973 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     2.85 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    1.64 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      3.18 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 4 Running wetted area 12.3711 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 0.04 thickness wing giving a 0.12 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in pitch is    1.64 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      3.17 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 4 Running wetted area 12.5449 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     2.83 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    1.64 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      3.16 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 Stab Running wetted area 13.8276 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    2.69 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      3.75 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 15.1103 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     2.66 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    3.32 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      4.18 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.

Vert Stab 1 Running wetted area 16.5780 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     2.60 m, based on mass-distribution across the shell of the craft with the 0.03 thickness wing giving a 0.11 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in pitch is    3.66 m, based on mass-distribution across the shell of the craft with the 0.03 thickness wing giving a 0.11 weighting per square meter on this flying surface.
	Running radius of gyration of the shell in yaw is      4.36 m, based on mass-distribution across the shell of the craft with the 0.03 thickness wing giving a 0.11 weighting per square meter on this flying surface.


Body 1 (fuselage):
	The frontal      area                          is  2.2704 m*m.
	The side         area                          is 26.7421 m*m.
	The top          area                          is 20.3936 m*m.
	The lateral      centroid                      is    0.00 m.
	The vertical     centroid                      is    0.14 m.
	The longitudinal centroid for lift at   0 slip is    4.43 m.
	The longitudinal centroid for lift at 180 slip is   13.16 meters

	Running wetted area 97.0723 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     1.28 m, based on mass-distribution across the shell of the craft.
	Running radius of gyration of the shell in pitch is    4.26 m, based on mass-distribution across the shell of the craft.
	Running radius of gyration of the shell in yaw is      4.35 m, based on mass-distribution across the shell of the craft.

Body 22 (inlet-left):
	The frontal      area                          is  1.7971 m*m.
	The side         area                          is 12.9955 m*m.
	The top          area                          is 11.7191 m*m.
	The lateral      centroid                      is    0.00 m.
	The vertical     centroid                      is   -0.23 m.
	The longitudinal centroid for lift at   0 slip is   -7.01 m.
	The longitudinal centroid for lift at 180 slip is   -2.54 meters

	Running wetted area 140.1010 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     1.18 m, based on mass-distribution across the shell of the craft.
	Running radius of gyration of the shell in pitch is    3.90 m, based on mass-distribution across the shell of the craft.
	Running radius of gyration of the shell in yaw is      3.94 m, based on mass-distribution across the shell of the craft.

Body 23 (inlet-right):
	The frontal      area                          is  1.7971 m*m.
	The side         area                          is 12.9955 m*m.
	The top          area                          is 11.7191 m*m.
	The lateral      centroid                      is    0.00 m.
	The vertical     centroid                      is   -0.23 m.
	The longitudinal centroid for lift at   0 slip is   -7.01 m.
	The longitudinal centroid for lift at 180 slip is   -2.54 meters

	Running wetted area 183.1296 square meters for all parts listed so far
	Running radius of gyration of the shell in roll is     1.22 m, based on mass-distribution across the shell of the craft.
	Running radius of gyration of the shell in pitch is    3.69 m, based on mass-distribution across the shell of the craft.
	Running radius of gyration of the shell in yaw is      3.73 m, based on mass-distribution across the shell of the craft.

Sum of all engines have mass of 3164.26 kg ( 24% of total):
	The radius of gyration of the engines in roll is     0.73 m, based on all engine masses and locations.
	The radius of gyration of the engines in pitch is    4.71 m, based on all engine masses and locations.
	The radius of gyration of the engines in yaw is      4.73 m, based on all engine masses and locations.

Sum of all tanks have mass of 309.35 kg (  2% of total):
	The radius of gyration of the tanks in roll is     1.17 m, based on all tank masses and locations.
	The radius of gyration of the tanks in pitch is    1.86 m, based on all tank masses and locations.
	The radius of gyration of the tanks in yaw is      2.09 m, based on all tank masses and locations.

Remainder of the craft has mass 9895.12 ( 74% of total):
	The radius of gyration of the shell in roll is     1.22 m, based on mass-distribution across the shell of the craft.
	The radius of gyration of the shell in pitch is    3.69 m, based on mass-distribution across the shell of the craft.
	The radius of gyration of the shell in yaw is      3.73 m, based on mass-distribution across the shell of the craft.

Final combined results:
	The radius of gyration in roll is     1.12 m. (that's moment of inertia 16750.779 kg*m*m).
	The radius of gyration in pitch is    3.92 m. (that's moment of inertia 205860.578 kg*m*m).
	The radius of gyration in yaw is      3.96 m. (that's moment of inertia 209874.219 kg*m*m).

Wing area           : 48.6487 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            :    4.84 m.   (For wings 1 through 4 only! This does not include stabilizers or misc wings!)
Long-arm of 25% MAC :   -0.46 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
••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••

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!)

