•••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••• Weapon Aircraft/330_JARDesign/Weapons/camera.wpn: •••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••• The frontal area is 0.000 square meters. The side area is 0.000 square meters. The top area is 0.000 square meters. The wetted area is 0.000 square meters. The longitudinal centroid is nan meters from the CG OF THE WEAPON. The lateral centroid is 0.000 meters from the CG OF THE WEAPON. The vertical centroid is nan meters from the CG OF THE WEAPON. The radius of gyration in roll is nan meters. The radius of gyration in pitch is nan meters. The radius of gyration in yaw is nan meters. •••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••• X-Plane, by Austin Meyer Simulating Aircraft/330_JARDesign/a330.acf •••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••• x location positive aft x force positive right pitch/alpha pos nose up y location positive right y force positive up roll pos right z location positive up z force positive aft yaw/beta pos nose right elevator, aileron, spoiler positive control surface up rudder positive control surface right drag-yaw positive control surface deployed pitch cyclic prop pitch positive request nose up roll cyclic prop pitch positive request nose right Finite-Wing & Element Build-Up for LEFT WING 1: root lo Re: A330.afl. root hi Re: A330.afl. tip lo Re: A330.afl. tip hi Re: A330.afl. Element # 0: S= 67.870 sqr mtrs, MAC= 9.70 mtrs, incidence= 0.00 deg. init wing side_S=67.87 NOTE! I AM ADDING LEFT WING 2 TO THE TIP OF LEFT WING 1 (through any intermediate wings) TO FORM ONE CONTINUOUS WING! (side_S=167.11) semilen joined=32.93, sweep25=27.44, side_S=167.11, AR=10.22 After any wing-joining, our semi-length is 32.93 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 11.67 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 2.44 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 30.89 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 27.44 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 10.22. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.21. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our washout is 0.00 deg. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root= 0.00 deg, tip= 0.00 deg) Oswalds efficiency is therefore 0.9946 Finite-Wing & Element Build-Up for RIGT WING 1: root lo Re: A330.afl. root hi Re: A330.afl. tip lo Re: A330.afl. tip hi Re: A330.afl. Element # 0: S= 67.870 sqr mtrs, MAC= 9.70 mtrs, incidence= 0.00 deg. init wing side_S=67.87 NOTE! I AM ADDING RIGT WING 2 TO THE TIP OF RIGT WING 1 (through any intermediate wings) TO FORM ONE CONTINUOUS WING! (side_S=167.11) semilen joined=32.93, sweep25=27.44, side_S=167.11, AR=10.22 After any wing-joining, our semi-length is 32.93 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 11.67 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 2.44 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 30.89 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 27.44 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 10.22. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.21. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our washout is 0.00 deg. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root= 0.00 deg, tip= 0.00 deg) Oswalds efficiency is therefore 0.9946 Finite-Wing & Element Build-Up for LEFT WING 2: root lo Re: A330.afl. root hi Re: A330.afl. tip lo Re: A330.afl. tip hi Re: A330.afl. Element # 0: S= 34.256 sqr mtrs, MAC= 6.86 mtrs, incidence= 0.00 deg. Element # 1: S= 27.958 sqr mtrs, MAC= 5.61 mtrs, incidence= 0.00 deg. Element # 2: S= 21.660 sqr mtrs, MAC= 4.35 mtrs, incidence= 0.00 deg. Element # 3: S= 15.363 sqr mtrs, MAC= 3.11 mtrs, incidence= 0.00 deg. init wing side_S=99.24 NOTE! I AM ADDING LEFT WING 1 TO THE ROOT OF LEFT WING 2 (through any intermediate wings) TO FORM ONE CONTINUOUS WING! (side_S=167.11) semilen joined=32.93, sweep25=27.44, side_S=167.11, AR=10.22 After any wing-joining, our semi-length is 32.93 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 11.67 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 2.44 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 30.89 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 27.44 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 10.22. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.21. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our washout is 0.00 deg. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root= 0.00 deg, tip= 0.00 deg) Oswalds efficiency is therefore 0.9946 Finite-Wing & Element Build-Up for RIGT WING 2: root lo Re: A330.afl. root hi Re: A330.afl. tip lo Re: A330.afl. tip hi Re: A330.afl. Element # 0: S= 34.256 sqr mtrs, MAC= 6.86 mtrs, incidence= 0.00 deg. Element # 1: S= 27.958 sqr mtrs, MAC= 5.61 mtrs, incidence= 0.00 deg. Element # 2: S= 21.660 sqr mtrs, MAC= 4.35 mtrs, incidence= 0.00 deg. Element # 3: S= 15.363 sqr mtrs, MAC= 3.11 mtrs, incidence= 0.00 deg. init wing side_S=99.24 NOTE! I AM ADDING RIGT WING 1 TO THE ROOT OF RIGT WING 2 (through any intermediate wings) TO FORM ONE CONTINUOUS WING! (side_S=167.11) semilen joined=32.93, sweep25=27.44, side_S=167.11, AR=10.22 After any wing-joining, our semi-length is 32.93 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 11.67 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 2.44 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 30.89 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 27.44 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 10.22. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.21. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our washout is 0.00 deg. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root= 0.00 deg, tip= 0.00 deg) Oswalds efficiency is therefore 0.9946 Finite-Wing & Element Build-Up for LEFT WING 3: root lo Re: A330.afl. root hi Re: A330.afl. tip lo Re: A330.afl. tip hi Re: A330.afl. Element # 0: S= 2.573 sqr mtrs, MAC= 1.85 mtrs, incidence= 0.00 deg. init wing side_S=2.57 semilen joined=30.14, sweep25=2.97, side_S=2.57, AR=704.01 After any wing-joining, our semi-length is 30.14 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 2.56 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 0.85 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 3.78 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 2.97 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 704.01. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.33. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our washout is 0.00 deg. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root= 0.00 deg, tip= 0.00 deg) Oswalds efficiency is therefore 0.9519 Finite-Wing & Element Build-Up for RIGT WING 3: root lo Re: A330.afl. root hi Re: A330.afl. tip lo Re: A330.afl. tip hi Re: A330.afl. Element # 0: S= 2.573 sqr mtrs, MAC= 1.85 mtrs, incidence= 0.00 deg. init wing side_S=2.57 semilen joined=30.14, sweep25=2.97, side_S=2.57, AR=704.01 After any wing-joining, our semi-length is 30.14 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 2.56 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 0.85 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 3.78 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 2.97 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 704.01. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.33. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our washout is 0.00 deg. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root= 0.00 deg, tip= 0.00 deg) Oswalds efficiency is therefore 0.9519 Finite-Wing & Element Build-Up for LEFT H STAB: root lo Re: NACA 0009 (symmetrical).afl. root hi Re: NACA 0009 (symmetrical).afl. tip lo Re: NACA 0009 (symmetrical).afl. tip hi Re: NACA 0009 (symmetrical).afl. Element # 0: S= 5.091 sqr mtrs, MAC= 5.67 mtrs, incidence= 0.00 deg. Element # 1: S= 4.763 sqr mtrs, MAC= 5.31 mtrs, incidence= 0.00 deg. Element # 2: S= 4.434 sqr mtrs, MAC= 4.94 mtrs, incidence= 0.00 deg. Element # 3: S= 4.106 sqr mtrs, MAC= 4.57 mtrs, incidence= 0.00 deg. Element # 4: S= 3.777 sqr mtrs, MAC= 4.21 mtrs, incidence= 0.00 deg. Element # 5: S= 3.449 sqr mtrs, MAC= 3.84 mtrs, incidence= 0.00 deg. Element # 6: S= 3.120 sqr mtrs, MAC= 3.48 mtrs, incidence= 0.00 deg. Element # 7: S= 2.792 sqr mtrs, MAC= 3.11 mtrs, incidence= 0.00 deg. Element # 8: S= 2.463 sqr mtrs, MAC= 2.75 mtrs, incidence= 0.00 deg. Element # 9: S= 2.135 sqr mtrs, MAC= 2.38 mtrs, incidence= 0.00 deg. init wing side_S=36.13 semilen joined=10.45, sweep25=30.80, side_S=36.13, AR=4.46 After any wing-joining, our semi-length is 10.45 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 5.85 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 2.19 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 34.91 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 30.80 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 4.46. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.37. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our washout is 0.00 deg. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root= 0.00 deg, tip= 0.00 deg) Oswalds efficiency is therefore 0.9891 Finite-Wing & Element Build-Up for RIGT H STAB: root lo Re: NACA 0009 (symmetrical).afl. root hi Re: NACA 0009 (symmetrical).afl. tip lo Re: NACA 0009 (symmetrical).afl. tip hi Re: NACA 0009 (symmetrical).afl. Element # 0: S= 5.091 sqr mtrs, MAC= 5.67 mtrs, incidence= 0.00 deg. Element # 1: S= 4.763 sqr mtrs, MAC= 5.31 mtrs, incidence= 0.00 deg. Element # 2: S= 4.434 sqr mtrs, MAC= 4.94 mtrs, incidence= 0.00 deg. Element # 3: S= 4.106 sqr mtrs, MAC= 4.57 mtrs, incidence= 0.00 deg. Element # 4: S= 3.777 sqr mtrs, MAC= 4.21 mtrs, incidence= 0.00 deg. Element # 5: S= 3.449 sqr mtrs, MAC= 3.84 mtrs, incidence= 0.00 deg. Element # 6: S= 3.120 sqr mtrs, MAC= 3.48 mtrs, incidence= 0.00 deg. Element # 7: S= 2.792 sqr mtrs, MAC= 3.11 mtrs, incidence= 0.00 deg. Element # 8: S= 2.463 sqr mtrs, MAC= 2.75 mtrs, incidence= 0.00 deg. Element # 9: S= 2.135 sqr mtrs, MAC= 2.38 mtrs, incidence= 0.00 deg. init wing side_S=36.13 semilen joined=10.45, sweep25=30.80, side_S=36.13, AR=4.46 After any wing-joining, our semi-length is 10.45 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 5.85 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 2.19 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 34.91 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 30.80 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 4.46. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.37. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our washout is 0.00 deg. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root= 0.00 deg, tip= 0.00 deg) Oswalds efficiency is therefore 0.9891 Finite-Wing & Element Build-Up for VERT STAB 1: root lo Re: NACA 0009 (symmetrical).afl. root hi Re: NACA 0009 (symmetrical).afl. tip lo Re: NACA 0009 (symmetrical).afl. tip hi Re: NACA 0009 (symmetrical).afl. Element # 0: S= 53.960 sqr mtrs, MAC= 6.54 mtrs, incidence= 0.00 deg. init wing side_S=53.96 semilen joined=11.73, sweep25=41.10, side_S=53.96, AR=2.90 After any wing-joining, our semi-length is 11.73 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 8.93 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 3.27 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 45.91 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 41.10 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 2.90. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.37. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our washout is 0.00 deg. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root= 0.00 deg, tip= 0.00 deg) Oswalds efficiency is therefore 0.9838 Finite-Wing & Element Build-Up for ENG PYLN 1a: root lo Re: NACA 0009 (symmetrical).afl. root hi Re: NACA 0009 (symmetrical).afl. tip lo Re: NACA 0009 (symmetrical).afl. tip hi Re: NACA 0009 (symmetrical).afl. Element # 0: S= 8.785 sqr mtrs, MAC= 5.18 mtrs, incidence= 0.00 deg. init wing side_S=8.78 semilen joined=5.49, sweep25=72.00, side_S=8.78, AR=0.65 Applying biplane interference factor to Oswalds Efficiency! between ENG PYLN 1a and ENG PYLN 2a. This takes e from 0.97 to 0.50. After any wing-joining, our semi-length is 5.49 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 5.18 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 5.18 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 72.00 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 72.00 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 0.65. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 1.00. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our washout is 0.00 deg. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root= 0.00 deg, tip= 0.00 deg) Oswalds efficiency is therefore 0.5000 Finite-Wing & Element Build-Up for ENG PYLN 2a: root lo Re: NACA 0009 (symmetrical).afl. root hi Re: NACA 0009 (symmetrical).afl. tip lo Re: NACA 0009 (symmetrical).afl. tip hi Re: NACA 0009 (symmetrical).afl. Element # 0: S= 8.785 sqr mtrs, MAC= 5.18 mtrs, incidence= 0.00 deg. init wing side_S=8.78 semilen joined=5.49, sweep25=72.00, side_S=8.78, AR=0.65 Applying biplane interference factor to Oswalds Efficiency! between ENG PYLN 2a and ENG PYLN 1a. This takes e from 0.97 to 0.50. After any wing-joining, our semi-length is 5.49 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 5.18 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 5.18 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 72.00 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 72.00 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 0.65. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 1.00. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our washout is 0.00 deg. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root= 0.00 deg, tip= 0.00 deg) Oswalds efficiency is therefore 0.5000 critical altitude=0.0000 mtrs, rho at crit alt=1.2250 kg/mmm, rho at SL=1.2250 kg/mmm, engine power boosted to 1.0000 of original. After LEFT WING 1, the RUNNING TOTAL wetted area is 67.870 square meters for all wings listed so far. After RIGT WING 1, the RUNNING TOTAL wetted area is 135.740 square meters for all wings listed so far. After LEFT WING 2, the RUNNING TOTAL wetted area is 234.976 square meters for all wings listed so far. After RIGT WING 2, the RUNNING TOTAL wetted area is 334.213 square meters for all wings listed so far. After LEFT WING 3, the RUNNING TOTAL wetted area is 336.786 square meters for all wings listed so far. After RIGT WING 3, the RUNNING TOTAL wetted area is 339.359 square meters for all wings listed so far. After LEFT H STAB, the RUNNING TOTAL wetted area is 375.490 square meters for all wings listed so far. After RIGT H STAB, the RUNNING TOTAL wetted area is 411.620 square meters for all wings listed so far. After VERT STAB 1, the RUNNING TOTAL wetted area is 465.580 square meters for all wings listed so far. After ENG PYLN 1a, the RUNNING TOTAL wetted area is 474.365 square meters for all wings listed so far. After ENG PYLN 2a, the RUNNING TOTAL wetted area is 483.150 square meters for all wings listed so far. Now for MI from FUSELAGE: The frontal area is 23.660 square meters. The side area is 272.929 square meters. The top area is 252.397 square meters. The RUNNING TOTAL wetted area is 1316.380 square meters, for the entire craft, including all wings, top and bottom surfaces, and all bodies listed so far. The longitudinal centroid is 0.028 meters. The lateral centroid is 0.000 meters. The vertical centroid is 1.494 meters. The radius of gyration in roll is 6.54 meters. The radius of gyration in pitch is 13.17 meters. The radius of gyration in yaw is 14.25 meters. Now for MI from MISC BODY 1: The frontal area is 21.756 square meters. The side area is 70.816 square meters. The top area is 123.535 square meters. The RUNNING TOTAL wetted area is 1656.267 square meters, for the entire craft, including all wings, top and bottom surfaces, and all bodies listed so far. The longitudinal centroid is -1.064 meters. The lateral centroid is 0.000 meters. The vertical centroid is -0.191 meters. The radius of gyration in roll is 5.95 meters. The radius of gyration in pitch is 11.98 meters. The radius of gyration in yaw is 12.95 meters. Now for MI from NACELLE 1: The frontal area is 7.823 square meters. The side area is 17.239 square meters. The top area is 17.682 square meters. The RUNNING TOTAL wetted area is 1718.956 square meters, for the entire craft, including all wings, top and bottom surfaces, and all bodies listed so far. The longitudinal centroid is -5.789 meters. The lateral centroid is -9.144 meters. The vertical centroid is -1.562 meters. The radius of gyration in roll is 6.06 meters. The radius of gyration in pitch is 11.82 meters. The radius of gyration in yaw is 12.86 meters. Now for MI from NACELLE 2: The frontal area is 7.823 square meters. The side area is 17.239 square meters. The top area is 17.682 square meters. The RUNNING TOTAL wetted area is 1781.644 square meters, for the entire craft, including all wings, top and bottom surfaces, and all bodies listed so far. The longitudinal centroid is -5.789 meters. The lateral centroid is 9.144 meters. The vertical centroid is -1.562 meters. The radius of gyration in roll is 6.25 meters. The radius of gyration in pitch is 11.67 meters. The radius of gyration in yaw is 12.82 meters. Engines have mass 11610.15 kg (9.34% of total): The radius of gyration of the engines in roll is 9.27 m, based on all engine powers/thrusts and locations. The radius of gyration of the engines in pitch is 1.78 m, based on all engine powers/thrusts and locations. The radius of gyration of the engines in yaw is 9.19 m, based on all engine powers/thrusts and locations. Remainder of the craft has mass 112674.19 (90.66% of total): The radius of gyration of the shell in roll is 6.25 m, based on mass-distribution across the shell of the craft with a 50% weighting on all of the flying surfaces. The radius of gyration of the shell in pitch is 11.67 m, based on mass-distribution across the shell of the craft with a 50% weighting on all of the flying surfaces. The radius of gyration of the shell in yaw is 12.82 m, based on mass-distribution across the shell of the craft with a 50% weighting on all of the flying surfaces. Final combined results: The radius of gyration in roll is 6.59 m. The radius of gyration in pitch is 11.13 m. The radius of gyration in yaw is 12.53 m. For LEFT WING 1: Full slat #1 deployment will cause coefficient data to spread out alpha-wise to 153.33% of original. Full slat #1 deployment will also change the lift coefficient by the same amount (keeping the lift SLOPE the same). For RIGT WING 1: Full slat #1 deployment will cause coefficient data to spread out alpha-wise to 153.33% of original. Full slat #1 deployment will also change the lift coefficient by the same amount (keeping the lift SLOPE the same). For LEFT WING 2: Full slat #1 deployment will cause coefficient data to spread out alpha-wise to 153.33% of original. Full slat #1 deployment will also change the lift coefficient by the same amount (keeping the lift SLOPE the same). For RIGT WING 2: Full slat #1 deployment will cause coefficient data to spread out alpha-wise to 153.33% of original. Full slat #1 deployment will also change the lift coefficient by the same amount (keeping the lift SLOPE the same). The centroid of all foils is at 5.42 m (positive aft from CG) when the 25% chord is assumed to be the element location.