•••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••• Weapon Aircraft/A320neoJD_V2/320neo_JARDesign/Weapons/crash.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. •••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••• Weapon Aircraft/A320neoJD_V2/320neo_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/A320neoJD_V2/320neo_JARDesign/a320neo.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: A318.afl. root hi Re: A318.afl. tip lo Re: A318.afl. tip hi Re: A318.afl. Element # 0: S= 4.342 sqr mtrs, MAC= 6.22 mtrs, incidence= 3.00 deg. Element # 1: S= 4.080 sqr mtrs, MAC= 5.84 mtrs, incidence= 3.00 deg. Element # 2: S= 3.819 sqr mtrs, MAC= 5.47 mtrs, incidence= 3.00 deg. Element # 3: S= 3.557 sqr mtrs, MAC= 5.09 mtrs, incidence= 3.00 deg. Element # 4: S= 3.295 sqr mtrs, MAC= 4.72 mtrs, incidence= 3.00 deg. Element # 5: S= 3.034 sqr mtrs, MAC= 4.34 mtrs, incidence= 3.00 deg. Element # 6: S= 2.772 sqr mtrs, MAC= 3.97 mtrs, incidence= 3.00 deg. init wing side_S=24.90 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=52.21) NOTE! I AM ADDING LEFT WING 3 TO THE TIP OF LEFT WING 1 (through any intermediate wings) TO FORM ONE CONTINUOUS WING! (side_S=53.58) semilen joined=19.14, sweep25=22.95, side_S=53.58, AR=11.60 After any wing-joining, our semi-length is 19.14 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 6.40 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 1.00 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 26.57 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 22.95 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 11.60. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.16. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our washout is 3.00 deg. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root= 3.00 deg, tip= 0.00 deg) Oswalds efficiency is therefore 0.9487 Finite-Wing & Element Build-Up for RIGT WING 1: root lo Re: A318.afl. root hi Re: A318.afl. tip lo Re: A318.afl. tip hi Re: A318.afl. Element # 0: S= 4.342 sqr mtrs, MAC= 6.22 mtrs, incidence= 3.00 deg. Element # 1: S= 4.080 sqr mtrs, MAC= 5.84 mtrs, incidence= 3.00 deg. Element # 2: S= 3.819 sqr mtrs, MAC= 5.47 mtrs, incidence= 3.00 deg. Element # 3: S= 3.557 sqr mtrs, MAC= 5.09 mtrs, incidence= 3.00 deg. Element # 4: S= 3.295 sqr mtrs, MAC= 4.72 mtrs, incidence= 3.00 deg. Element # 5: S= 3.034 sqr mtrs, MAC= 4.34 mtrs, incidence= 3.00 deg. Element # 6: S= 2.772 sqr mtrs, MAC= 3.97 mtrs, incidence= 3.00 deg. init wing side_S=24.90 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=52.21) NOTE! I AM ADDING RIGT WING 3 TO THE TIP OF RIGT WING 1 (through any intermediate wings) TO FORM ONE CONTINUOUS WING! (side_S=53.58) semilen joined=19.14, sweep25=22.95, side_S=53.58, AR=11.60 After any wing-joining, our semi-length is 19.14 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 6.40 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 1.00 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 26.57 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 22.95 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 11.60. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.16. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our washout is 3.00 deg. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root= 3.00 deg, tip= 0.00 deg) Oswalds efficiency is therefore 0.9487 Finite-Wing & Element Build-Up for LEFT WING 2: root lo Re: A318.afl. root hi Re: A318.afl. tip lo Re: A318.afl. tip hi Re: A318.afl. Element # 0: S= 3.746 sqr mtrs, MAC= 3.67 mtrs, incidence= 3.00 deg. Element # 1: S= 3.520 sqr mtrs, MAC= 3.45 mtrs, incidence= 2.70 deg. Element # 2: S= 3.295 sqr mtrs, MAC= 3.23 mtrs, incidence= 2.40 deg. Element # 3: S= 3.069 sqr mtrs, MAC= 3.01 mtrs, incidence= 2.10 deg. Element # 4: S= 2.844 sqr mtrs, MAC= 2.79 mtrs, incidence= 1.80 deg. Element # 5: S= 2.618 sqr mtrs, MAC= 2.57 mtrs, incidence= 1.50 deg. Element # 6: S= 2.392 sqr mtrs, MAC= 2.34 mtrs, incidence= 1.20 deg. Element # 7: S= 2.167 sqr mtrs, MAC= 2.12 mtrs, incidence= 0.90 deg. Element # 8: S= 1.941 sqr mtrs, MAC= 1.90 mtrs, incidence= 0.60 deg. Element # 9: S= 1.715 sqr mtrs, MAC= 1.68 mtrs, incidence= 0.30 deg. init wing side_S=27.31 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=52.21) NOTE! I AM ADDING LEFT WING 3 TO THE TIP OF LEFT WING 2 (through any intermediate wings) TO FORM ONE CONTINUOUS WING! (side_S=53.58) semilen joined=19.14, sweep25=22.95, side_S=53.58, AR=11.60 After any wing-joining, our semi-length is 19.14 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 6.40 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 1.00 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 26.57 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 22.95 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 11.60. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.16. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our washout is 3.00 deg. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root= 3.00 deg, tip= 0.00 deg) Oswalds efficiency is therefore 0.9487 Finite-Wing & Element Build-Up for RIGT WING 2: root lo Re: A318.afl. root hi Re: A318.afl. tip lo Re: A318.afl. tip hi Re: A318.afl. Element # 0: S= 3.746 sqr mtrs, MAC= 3.67 mtrs, incidence= 3.00 deg. Element # 1: S= 3.520 sqr mtrs, MAC= 3.45 mtrs, incidence= 2.70 deg. Element # 2: S= 3.295 sqr mtrs, MAC= 3.23 mtrs, incidence= 2.40 deg. Element # 3: S= 3.069 sqr mtrs, MAC= 3.01 mtrs, incidence= 2.10 deg. Element # 4: S= 2.844 sqr mtrs, MAC= 2.79 mtrs, incidence= 1.80 deg. Element # 5: S= 2.618 sqr mtrs, MAC= 2.57 mtrs, incidence= 1.50 deg. Element # 6: S= 2.392 sqr mtrs, MAC= 2.34 mtrs, incidence= 1.20 deg. Element # 7: S= 2.167 sqr mtrs, MAC= 2.12 mtrs, incidence= 0.90 deg. Element # 8: S= 1.941 sqr mtrs, MAC= 1.90 mtrs, incidence= 0.60 deg. Element # 9: S= 1.715 sqr mtrs, MAC= 1.68 mtrs, incidence= 0.30 deg. init wing side_S=27.31 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=52.21) NOTE! I AM ADDING RIGT WING 3 TO THE TIP OF RIGT WING 2 (through any intermediate wings) TO FORM ONE CONTINUOUS WING! (side_S=53.58) semilen joined=19.14, sweep25=22.95, side_S=53.58, AR=11.60 After any wing-joining, our semi-length is 19.14 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 6.40 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 1.00 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 26.57 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 22.95 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 11.60. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.16. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our washout is 3.00 deg. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root= 3.00 deg, tip= 0.00 deg) Oswalds efficiency is therefore 0.9487 Finite-Wing & Element Build-Up for LEFT WING 3: root lo Re: A318.afl. root hi Re: A318.afl. tip lo Re: A318.afl. tip hi Re: A318.afl. Element # 0: S= 1.373 sqr mtrs, MAC= 1.32 mtrs, incidence= 0.00 deg. init wing side_S=1.37 NOTE! I AM ADDING LEFT WING 2 TO THE ROOT OF LEFT WING 3 (through any intermediate wings) TO FORM ONE CONTINUOUS WING! (side_S=28.68) NOTE! I AM ADDING LEFT WING 1 TO THE ROOT OF LEFT WING 3 (through any intermediate wings) TO FORM ONE CONTINUOUS WING! (side_S=53.58) semilen joined=19.14, sweep25=22.95, side_S=53.58, AR=11.60 After any wing-joining, our semi-length is 19.14 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 6.40 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 1.00 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 26.57 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 22.95 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 11.60. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.16. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our washout is 3.00 deg. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root= 3.00 deg, tip= 0.00 deg) Oswalds efficiency is therefore 0.9487 Finite-Wing & Element Build-Up for RIGT WING 3: root lo Re: A318.afl. root hi Re: A318.afl. tip lo Re: A318.afl. tip hi Re: A318.afl. Element # 0: S= 1.373 sqr mtrs, MAC= 1.32 mtrs, incidence= 0.00 deg. init wing side_S=1.37 NOTE! I AM ADDING RIGT WING 2 TO THE ROOT OF RIGT WING 3 (through any intermediate wings) TO FORM ONE CONTINUOUS WING! (side_S=28.68) NOTE! I AM ADDING RIGT WING 1 TO THE ROOT OF RIGT WING 3 (through any intermediate wings) TO FORM ONE CONTINUOUS WING! (side_S=53.58) semilen joined=19.14, sweep25=22.95, side_S=53.58, AR=11.60 After any wing-joining, our semi-length is 19.14 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 6.40 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 1.00 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 26.57 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 22.95 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 11.60. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.16. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our washout is 3.00 deg. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root= 3.00 deg, tip= 0.00 deg) Oswalds efficiency is therefore 0.9487 Finite-Wing & Element Build-Up for LEFT WING 4: 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= 1.279 sqr mtrs, MAC= 0.69 mtrs, incidence= 0.00 deg. init wing side_S=1.28 semilen joined=2.60, sweep25=35.00, side_S=1.28, AR=7.09 After any wing-joining, our semi-length is 2.60 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 1.00 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 0.20 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 38.45 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 35.00 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 7.09. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.20. (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 0.9948 Finite-Wing & Element Build-Up for RIGT WING 4: 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= 1.279 sqr mtrs, MAC= 0.69 mtrs, incidence= 0.00 deg. init wing side_S=1.28 semilen joined=2.60, sweep25=35.00, side_S=1.28, AR=7.09 After any wing-joining, our semi-length is 2.60 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 1.00 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 0.20 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 38.45 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 35.00 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 7.09. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.20. (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 0.9948 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= 1.928 sqr mtrs, MAC= 3.48 mtrs, incidence= 1.00 deg. Element # 1: S= 1.796 sqr mtrs, MAC= 3.24 mtrs, incidence= 1.00 deg. Element # 2: S= 1.664 sqr mtrs, MAC= 3.01 mtrs, incidence= 1.00 deg. Element # 3: S= 1.533 sqr mtrs, MAC= 2.77 mtrs, incidence= 1.00 deg. Element # 4: S= 1.401 sqr mtrs, MAC= 2.53 mtrs, incidence= 1.00 deg. Element # 5: S= 1.269 sqr mtrs, MAC= 2.29 mtrs, incidence= 1.00 deg. Element # 6: S= 1.137 sqr mtrs, MAC= 2.05 mtrs, incidence= 1.00 deg. Element # 7: S= 1.005 sqr mtrs, MAC= 1.82 mtrs, incidence= 1.00 deg. Element # 8: S= 0.873 sqr mtrs, MAC= 1.58 mtrs, incidence= 1.00 deg. Element # 9: S= 0.741 sqr mtrs, MAC= 1.34 mtrs, incidence= 1.00 deg. init wing side_S=13.35 semilen joined=6.96, sweep25=25.73, side_S=13.35, AR=5.88 After any wing-joining, our semi-length is 6.96 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 3.60 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 1.22 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 29.98 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 25.73 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 5.88. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.34. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our washout is 0.00 deg. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root= 1.00 deg, tip= 1.00 deg) Oswalds efficiency is therefore 0.9932 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= 1.928 sqr mtrs, MAC= 3.48 mtrs, incidence= 1.00 deg. Element # 1: S= 1.796 sqr mtrs, MAC= 3.24 mtrs, incidence= 1.00 deg. Element # 2: S= 1.664 sqr mtrs, MAC= 3.01 mtrs, incidence= 1.00 deg. Element # 3: S= 1.533 sqr mtrs, MAC= 2.77 mtrs, incidence= 1.00 deg. Element # 4: S= 1.401 sqr mtrs, MAC= 2.53 mtrs, incidence= 1.00 deg. Element # 5: S= 1.269 sqr mtrs, MAC= 2.29 mtrs, incidence= 1.00 deg. Element # 6: S= 1.137 sqr mtrs, MAC= 2.05 mtrs, incidence= 1.00 deg. Element # 7: S= 1.005 sqr mtrs, MAC= 1.82 mtrs, incidence= 1.00 deg. Element # 8: S= 0.873 sqr mtrs, MAC= 1.58 mtrs, incidence= 1.00 deg. Element # 9: S= 0.741 sqr mtrs, MAC= 1.34 mtrs, incidence= 1.00 deg. init wing side_S=13.35 semilen joined=6.96, sweep25=25.73, side_S=13.35, AR=5.88 After any wing-joining, our semi-length is 6.96 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 3.60 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 1.22 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 29.98 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 25.73 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 5.88. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.34. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our washout is 0.00 deg. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root= 1.00 deg, tip= 1.00 deg) Oswalds efficiency is therefore 0.9932 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= 21.028 sqr mtrs, MAC= 3.69 mtrs, incidence= 0.00 deg. init wing side_S=21.03 semilen joined=7.57, sweep25=34.00, side_S=21.03, AR=3.74 After any wing-joining, our semi-length is 7.57 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 1.52 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 39.36 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 34.00 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 3.74. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.29. (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 0.9897 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 24.899 square meters for all wings listed so far. After RIGT WING 1, the RUNNING TOTAL wetted area is 49.797 square meters for all wings listed so far. After LEFT WING 2, the RUNNING TOTAL wetted area is 77.104 square meters for all wings listed so far. After RIGT WING 2, the RUNNING TOTAL wetted area is 104.411 square meters for all wings listed so far. After LEFT WING 3, the RUNNING TOTAL wetted area is 105.784 square meters for all wings listed so far. After RIGT WING 3, the RUNNING TOTAL wetted area is 107.156 square meters for all wings listed so far. After LEFT WING 4, the RUNNING TOTAL wetted area is 108.435 square meters for all wings listed so far. After RIGT WING 4, the RUNNING TOTAL wetted area is 109.714 square meters for all wings listed so far. After LEFT H STAB, the RUNNING TOTAL wetted area is 123.061 square meters for all wings listed so far. After RIGT H STAB, the RUNNING TOTAL wetted area is 136.408 square meters for all wings listed so far. After VERT STAB 1, the RUNNING TOTAL wetted area is 157.436 square meters for all wings listed so far. Now for MI from FUSELAGE: The frontal area is 12.233 square meters. The side area is 133.533 square meters. The top area is 124.030 square meters. The RUNNING TOTAL wetted area is 563.279 square meters, for the entire craft, including all wings, top and bottom surfaces, and all bodies listed so far. The longitudinal centroid is 1.355 meters. The lateral centroid is 0.000 meters. The vertical centroid is 1.485 meters. The radius of gyration in roll is 3.77 meters. The radius of gyration in pitch is 8.88 meters. The radius of gyration in yaw is 9.19 meters. Now for MI from MISC BODY 2: The frontal area is 7.452 square meters. The side area is 20.875 square meters. The top area is 43.416 square meters. The RUNNING TOTAL wetted area is 677.911 square meters, for the entire craft, including all wings, top and bottom surfaces, and all bodies listed so far. The longitudinal centroid is -0.433 meters. The lateral centroid is 0.000 meters. The vertical centroid is 0.199 meters. The radius of gyration in roll is 3.49 meters. The radius of gyration in pitch is 8.21 meters. The radius of gyration in yaw is 8.50 meters. Now for MI from NACELLE 1: The frontal area is 2.983 square meters. The side area is 8.670 square meters. The top area is 10.145 square meters. The RUNNING TOTAL wetted area is 712.071 square meters, for the entire craft, including all wings, top and bottom surfaces, and all bodies listed so far. The longitudinal centroid is -3.126 meters. The lateral centroid is -5.791 meters. The vertical centroid is -0.693 meters. The radius of gyration in roll is 3.61 meters. The radius of gyration in pitch is 8.05 meters. The radius of gyration in yaw is 8.40 meters. Now for MI from NACELLE 2: The frontal area is 2.983 square meters. The side area is 8.670 square meters. The top area is 10.145 square meters. The RUNNING TOTAL wetted area is 746.230 square meters, for the entire craft, including all wings, top and bottom surfaces, and all bodies listed so far. The longitudinal centroid is -3.126 meters. The lateral centroid is 5.791 meters. The vertical centroid is -0.693 meters. The radius of gyration in roll is 3.78 meters. The radius of gyration in pitch is 7.89 meters. The radius of gyration in yaw is 8.35 meters. Now for MI from W-FAIRING 1: The frontal area is 0.048 square meters. The side area is 0.158 square meters. The top area is 0.209 square meters. The RUNNING TOTAL wetted area is 747.010 square meters, for the entire craft, including all wings, top and bottom surfaces, and all bodies listed so far. The longitudinal centroid is -10.711 meters. The lateral centroid is 0.000 meters. The vertical centroid is -2.367 meters. The radius of gyration in roll is 3.78 meters. The radius of gyration in pitch is 7.90 meters. The radius of gyration in yaw is 8.35 meters. Engines have mass 4408.92 kg (10.75% of total): The radius of gyration of the engines in roll is 5.83 m, based on all engine powers/thrusts and locations. The radius of gyration of the engines in pitch is 1.22 m, based on all engine powers/thrusts and locations. The radius of gyration of the engines in yaw is 5.88 m, based on all engine powers/thrusts and locations. Remainder of the craft has mass 36591.08 (89.25% of total): The radius of gyration of the shell in roll is 3.78 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 7.90 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 8.35 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 4.05 m. The radius of gyration in pitch is 7.47 m. The radius of gyration in yaw is 8.12 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 #2 deployment will cause coefficient data to spread out alpha-wise to 153.33% of original. Full slat #2 deployment will also change the lift coefficient by the same amount (keeping the lift SLOPE the same). For RIGT WING 2: Full slat #2 deployment will cause coefficient data to spread out alpha-wise to 153.33% of original. Full slat #2 deployment will also change the lift coefficient by the same amount (keeping the lift SLOPE the same). The centroid of all foils is at 5.17 m (positive aft from CG) when the 25% chord is assumed to be the element location. The centroid of all foils is at 5.22 m (positive aft from CG) when the wing is looked at partially as a delta-wing based on taper ratio. The average chord of all foils is 3.06 m. So you could say the static margin is 1.69 (positive stable) when the 25% chord is assumed to be the element location. So you could say the static margin is 1.70 (positive stable) when the wing is looked at partially as a delta-wing based on taper ratio.