•••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••• X-Plane, by Austin Meyer Simulating Aircraft/Heavy Metal/B747-400 United/747-400 United.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: Boeing Root (high subsonic).afl. root hi Re: Boeing Root (high subsonic).afl. tip lo Re: Boeing Mid (high subsonic).afl. tip hi Re: Boeing Mid (high subsonic).afl. Element # 0: S= 18.218 sqr mtrs, MAC= 16.16 mtrs, incidence= 3.00 deg. Element # 1: S= 17.473 sqr mtrs, MAC= 15.50 mtrs, incidence= 3.50 deg. Element # 2: S= 16.727 sqr mtrs, MAC= 14.84 mtrs, incidence= 4.00 deg. Element # 3: S= 15.981 sqr mtrs, MAC= 14.18 mtrs, incidence= 4.00 deg. Element # 4: S= 15.235 sqr mtrs, MAC= 13.52 mtrs, incidence= 3.80 deg. Element # 5: S= 14.490 sqr mtrs, MAC= 12.85 mtrs, incidence= 3.60 deg. Element # 6: S= 13.744 sqr mtrs, MAC= 12.19 mtrs, incidence= 3.40 deg. Element # 7: S= 12.998 sqr mtrs, MAC= 11.53 mtrs, incidence= 3.30 deg. Element # 8: S= 12.253 sqr mtrs, MAC= 10.87 mtrs, incidence= 3.00 deg. Element # 9: S= 11.507 sqr mtrs, MAC= 10.21 mtrs, incidence= 2.80 deg. init wing side_S=148.63 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=165.48) 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=233.11) NOTE! I AM ADDING LEFT WING 4 TO THE TIP OF LEFT WING 1 (through any intermediate wings) TO FORM ONE CONTINUOUS WING! (side_S=271.63) semilen joined=37.93, sweep25=37.84, side_S=271.63, AR=6.61 After any wing-joining, our semi-length is 37.93 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 16.49 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 4.08 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 41.36 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 37.84 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 6.61. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.25. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our washout is 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 0.9879 Finite-Wing & Element Build-Up for RIGT WING 1: root lo Re: Boeing Root (high subsonic).afl. root hi Re: Boeing Root (high subsonic).afl. tip lo Re: Boeing Mid (high subsonic).afl. tip hi Re: Boeing Mid (high subsonic).afl. Element # 0: S= 18.218 sqr mtrs, MAC= 16.16 mtrs, incidence= 3.00 deg. Element # 1: S= 17.473 sqr mtrs, MAC= 15.50 mtrs, incidence= 3.50 deg. Element # 2: S= 16.727 sqr mtrs, MAC= 14.84 mtrs, incidence= 4.00 deg. Element # 3: S= 15.981 sqr mtrs, MAC= 14.18 mtrs, incidence= 4.00 deg. Element # 4: S= 15.235 sqr mtrs, MAC= 13.52 mtrs, incidence= 3.80 deg. Element # 5: S= 14.490 sqr mtrs, MAC= 12.85 mtrs, incidence= 3.60 deg. Element # 6: S= 13.744 sqr mtrs, MAC= 12.19 mtrs, incidence= 3.40 deg. Element # 7: S= 12.998 sqr mtrs, MAC= 11.53 mtrs, incidence= 3.30 deg. Element # 8: S= 12.253 sqr mtrs, MAC= 10.87 mtrs, incidence= 3.00 deg. Element # 9: S= 11.507 sqr mtrs, MAC= 10.21 mtrs, incidence= 2.80 deg. init wing side_S=148.63 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=165.48) 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=233.11) NOTE! I AM ADDING RIGT WING 4 TO THE TIP OF RIGT WING 1 (through any intermediate wings) TO FORM ONE CONTINUOUS WING! (side_S=271.63) semilen joined=37.93, sweep25=37.84, side_S=271.63, AR=6.61 After any wing-joining, our semi-length is 37.93 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 16.49 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 4.08 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 41.36 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 37.84 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 6.61. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.25. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our washout is 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 0.9879 Finite-Wing & Element Build-Up for LEFT WING 2: root lo Re: Boeing Mid (high subsonic).afl. root hi Re: Boeing Mid (high subsonic).afl. tip lo Re: Boeing Mid (high subsonic).afl. tip hi Re: Boeing Mid (high subsonic).afl. Element # 0: S= 4.393 sqr mtrs, MAC= 9.74 mtrs, incidence= 2.80 deg. Element # 1: S= 4.273 sqr mtrs, MAC= 9.48 mtrs, incidence= 2.80 deg. Element # 2: S= 4.152 sqr mtrs, MAC= 9.21 mtrs, incidence= 2.80 deg. Element # 3: S= 4.032 sqr mtrs, MAC= 8.94 mtrs, incidence= 2.80 deg. init wing side_S=16.85 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=165.48) 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=233.11) NOTE! I AM ADDING LEFT WING 4 TO THE TIP OF LEFT WING 2 (through any intermediate wings) TO FORM ONE CONTINUOUS WING! (side_S=271.63) semilen joined=37.93, sweep25=37.84, side_S=271.63, AR=6.61 After any wing-joining, our semi-length is 37.93 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 16.49 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 4.08 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 41.36 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 37.84 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 6.61. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.25. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our washout is 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 0.9879 Finite-Wing & Element Build-Up for RIGT WING 2: root lo Re: Boeing Mid (high subsonic).afl. root hi Re: Boeing Mid (high subsonic).afl. tip lo Re: Boeing Mid (high subsonic).afl. tip hi Re: Boeing Mid (high subsonic).afl. Element # 0: S= 4.393 sqr mtrs, MAC= 9.74 mtrs, incidence= 2.80 deg. Element # 1: S= 4.273 sqr mtrs, MAC= 9.48 mtrs, incidence= 2.80 deg. Element # 2: S= 4.152 sqr mtrs, MAC= 9.21 mtrs, incidence= 2.80 deg. Element # 3: S= 4.032 sqr mtrs, MAC= 8.94 mtrs, incidence= 2.80 deg. init wing side_S=16.85 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=165.48) 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=233.11) NOTE! I AM ADDING RIGT WING 4 TO THE TIP OF RIGT WING 2 (through any intermediate wings) TO FORM ONE CONTINUOUS WING! (side_S=271.63) semilen joined=37.93, sweep25=37.84, side_S=271.63, AR=6.61 After any wing-joining, our semi-length is 37.93 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 16.49 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 4.08 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 41.36 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 37.84 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 6.61. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.25. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our washout is 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 0.9879 Finite-Wing & Element Build-Up for LEFT WING 3: root lo Re: Boeing Mid (high subsonic).afl. root hi Re: Boeing Mid (high subsonic).afl. tip lo Re: Boeing Mid (high subsonic).afl. tip hi Re: Boeing Mid (high subsonic).afl. Element # 0: S= 7.961 sqr mtrs, MAC= 8.66 mtrs, incidence= 2.80 deg. Element # 1: S= 7.695 sqr mtrs, MAC= 8.38 mtrs, incidence= 2.50 deg. Element # 2: S= 7.429 sqr mtrs, MAC= 8.09 mtrs, incidence= 2.20 deg. Element # 3: S= 7.163 sqr mtrs, MAC= 7.80 mtrs, incidence= 1.80 deg. Element # 4: S= 6.896 sqr mtrs, MAC= 7.51 mtrs, incidence= 1.50 deg. Element # 5: S= 6.630 sqr mtrs, MAC= 7.22 mtrs, incidence= 1.30 deg. Element # 6: S= 6.364 sqr mtrs, MAC= 6.93 mtrs, incidence= 1.10 deg. Element # 7: S= 6.098 sqr mtrs, MAC= 6.64 mtrs, incidence= 1.00 deg. Element # 8: S= 5.832 sqr mtrs, MAC= 6.35 mtrs, incidence= 0.90 deg. Element # 9: S= 5.566 sqr mtrs, MAC= 6.06 mtrs, incidence= 0.80 deg. init wing side_S=67.63 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=84.48) NOTE! I AM ADDING LEFT WING 4 TO THE TIP OF LEFT WING 3 (through any intermediate wings) TO FORM ONE CONTINUOUS WING! (side_S=123.01) 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=271.63) semilen joined=37.93, sweep25=37.84, side_S=271.63, AR=6.61 After any wing-joining, our semi-length is 37.93 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 16.49 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 4.08 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 41.36 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 37.84 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 6.61. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.25. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our washout is 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 0.9879 Finite-Wing & Element Build-Up for RIGT WING 3: root lo Re: Boeing Mid (high subsonic).afl. root hi Re: Boeing Mid (high subsonic).afl. tip lo Re: Boeing Mid (high subsonic).afl. tip hi Re: Boeing Mid (high subsonic).afl. Element # 0: S= 7.961 sqr mtrs, MAC= 8.66 mtrs, incidence= 2.80 deg. Element # 1: S= 7.695 sqr mtrs, MAC= 8.38 mtrs, incidence= 2.50 deg. Element # 2: S= 7.429 sqr mtrs, MAC= 8.09 mtrs, incidence= 2.20 deg. Element # 3: S= 7.163 sqr mtrs, MAC= 7.80 mtrs, incidence= 1.80 deg. Element # 4: S= 6.896 sqr mtrs, MAC= 7.51 mtrs, incidence= 1.50 deg. Element # 5: S= 6.630 sqr mtrs, MAC= 7.22 mtrs, incidence= 1.30 deg. Element # 6: S= 6.364 sqr mtrs, MAC= 6.93 mtrs, incidence= 1.10 deg. Element # 7: S= 6.098 sqr mtrs, MAC= 6.64 mtrs, incidence= 1.00 deg. Element # 8: S= 5.832 sqr mtrs, MAC= 6.35 mtrs, incidence= 0.90 deg. Element # 9: S= 5.566 sqr mtrs, MAC= 6.06 mtrs, incidence= 0.80 deg. init wing side_S=67.63 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=84.48) NOTE! I AM ADDING RIGT WING 4 TO THE TIP OF RIGT WING 3 (through any intermediate wings) TO FORM ONE CONTINUOUS WING! (side_S=123.01) 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=271.63) semilen joined=37.93, sweep25=37.84, side_S=271.63, AR=6.61 After any wing-joining, our semi-length is 37.93 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 16.49 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 4.08 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 41.36 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 37.84 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 6.61. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.25. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our washout is 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 0.9879 Finite-Wing & Element Build-Up for LEFT WING 4: root lo Re: Boeing Mid (high subsonic).afl. root hi Re: Boeing Mid (high subsonic).afl. tip lo Re: Boeing Tip (high subsonic).afl. tip hi Re: Boeing Tip (high subsonic).afl. Element # 0: S= 4.486 sqr mtrs, MAC= 5.82 mtrs, incidence= 0.80 deg. Element # 1: S= 4.345 sqr mtrs, MAC= 5.64 mtrs, incidence= 0.70 deg. Element # 2: S= 4.205 sqr mtrs, MAC= 5.46 mtrs, incidence= 0.50 deg. Element # 3: S= 4.064 sqr mtrs, MAC= 5.27 mtrs, incidence= 0.40 deg. Element # 4: S= 3.923 sqr mtrs, MAC= 5.09 mtrs, incidence= 0.30 deg. Element # 5: S= 3.782 sqr mtrs, MAC= 4.91 mtrs, incidence= 0.20 deg. Element # 6: S= 3.641 sqr mtrs, MAC= 4.72 mtrs, incidence= 0.10 deg. Element # 7: S= 3.500 sqr mtrs, MAC= 4.54 mtrs, incidence= 0.00 deg. Element # 8: S= 3.359 sqr mtrs, MAC= 4.36 mtrs, incidence= 0.00 deg. Element # 9: S= 3.218 sqr mtrs, MAC= 4.18 mtrs, incidence= 0.00 deg. init wing side_S=38.52 NOTE! I AM ADDING LEFT WING 3 TO THE ROOT OF LEFT WING 4 (through any intermediate wings) TO FORM ONE CONTINUOUS WING! (side_S=106.16) NOTE! I AM ADDING LEFT WING 2 TO THE ROOT OF LEFT WING 4 (through any intermediate wings) TO FORM ONE CONTINUOUS WING! (side_S=123.01) NOTE! I AM ADDING LEFT WING 1 TO THE ROOT OF LEFT WING 4 (through any intermediate wings) TO FORM ONE CONTINUOUS WING! (side_S=271.63) semilen joined=37.93, sweep25=37.84, side_S=271.63, AR=6.61 After any wing-joining, our semi-length is 37.93 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 16.49 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 4.08 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 41.36 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 37.84 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 6.61. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.25. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our washout is 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 0.9879 Finite-Wing & Element Build-Up for RIGT WING 4: root lo Re: Boeing Mid (high subsonic).afl. root hi Re: Boeing Mid (high subsonic).afl. tip lo Re: Boeing Tip (high subsonic).afl. tip hi Re: Boeing Tip (high subsonic).afl. Element # 0: S= 4.486 sqr mtrs, MAC= 5.82 mtrs, incidence= 0.80 deg. Element # 1: S= 4.345 sqr mtrs, MAC= 5.64 mtrs, incidence= 0.70 deg. Element # 2: S= 4.205 sqr mtrs, MAC= 5.46 mtrs, incidence= 0.50 deg. Element # 3: S= 4.064 sqr mtrs, MAC= 5.27 mtrs, incidence= 0.40 deg. Element # 4: S= 3.923 sqr mtrs, MAC= 5.09 mtrs, incidence= 0.30 deg. Element # 5: S= 3.782 sqr mtrs, MAC= 4.91 mtrs, incidence= 0.20 deg. Element # 6: S= 3.641 sqr mtrs, MAC= 4.72 mtrs, incidence= 0.10 deg. Element # 7: S= 3.500 sqr mtrs, MAC= 4.54 mtrs, incidence= 0.00 deg. Element # 8: S= 3.359 sqr mtrs, MAC= 4.36 mtrs, incidence= 0.00 deg. Element # 9: S= 3.218 sqr mtrs, MAC= 4.18 mtrs, incidence= 0.00 deg. init wing side_S=38.52 NOTE! I AM ADDING RIGT WING 3 TO THE ROOT OF RIGT WING 4 (through any intermediate wings) TO FORM ONE CONTINUOUS WING! (side_S=106.16) NOTE! I AM ADDING RIGT WING 2 TO THE ROOT OF RIGT WING 4 (through any intermediate wings) TO FORM ONE CONTINUOUS WING! (side_S=123.01) NOTE! I AM ADDING RIGT WING 1 TO THE ROOT OF RIGT WING 4 (through any intermediate wings) TO FORM ONE CONTINUOUS WING! (side_S=271.63) semilen joined=37.93, sweep25=37.84, side_S=271.63, AR=6.61 After any wing-joining, our semi-length is 37.93 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 16.49 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 4.08 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 41.36 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 37.84 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 6.61. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.25. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our washout is 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 0.9879 Finite-Wing & Element Build-Up for LEFT H STAB: root lo Re: NACA 2412 (popular) invert.afl. root hi Re: NACA 2412 (popular) invert.afl. tip lo Re: NACA 2412 (popular) invert.afl. tip hi Re: NACA 2412 (popular) invert.afl. Element # 0: S= 14.721 sqr mtrs, MAC= 9.30 mtrs, incidence= 0.00 deg. Element # 1: S= 13.066 sqr mtrs, MAC= 8.26 mtrs, incidence= 0.00 deg. Element # 2: S= 11.410 sqr mtrs, MAC= 7.21 mtrs, incidence= 0.00 deg. Element # 3: S= 9.754 sqr mtrs, MAC= 6.17 mtrs, incidence= 0.00 deg. Element # 4: S= 8.099 sqr mtrs, MAC= 5.13 mtrs, incidence= 0.00 deg. Element # 5: S= 6.443 sqr mtrs, MAC= 4.09 mtrs, incidence= 0.00 deg. Element # 6: S= 4.787 sqr mtrs, MAC= 3.05 mtrs, incidence= 0.00 deg. init wing side_S=68.28 semilen joined=13.96, sweep25=37.40, side_S=68.28, AR=3.60 After any wing-joining, our semi-length is 13.96 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 9.81 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 2.50 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 42.91 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 37.40 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 3.60. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.25. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our washout is 0.00 deg. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root= 0.00 deg, tip= 0.00 deg) Oswalds efficiency is therefore 0.9896 Finite-Wing & Element Build-Up for RIGT H STAB: root lo Re: NACA 2412 (popular) invert.afl. root hi Re: NACA 2412 (popular) invert.afl. tip lo Re: NACA 2412 (popular) invert.afl. tip hi Re: NACA 2412 (popular) invert.afl. Element # 0: S= 14.721 sqr mtrs, MAC= 9.30 mtrs, incidence= 0.00 deg. Element # 1: S= 13.066 sqr mtrs, MAC= 8.26 mtrs, incidence= 0.00 deg. Element # 2: S= 11.410 sqr mtrs, MAC= 7.21 mtrs, incidence= 0.00 deg. Element # 3: S= 9.754 sqr mtrs, MAC= 6.17 mtrs, incidence= 0.00 deg. Element # 4: S= 8.099 sqr mtrs, MAC= 5.13 mtrs, incidence= 0.00 deg. Element # 5: S= 6.443 sqr mtrs, MAC= 4.09 mtrs, incidence= 0.00 deg. Element # 6: S= 4.787 sqr mtrs, MAC= 3.05 mtrs, incidence= 0.00 deg. init wing side_S=68.28 semilen joined=13.96, sweep25=37.40, side_S=68.28, AR=3.60 After any wing-joining, our semi-length is 13.96 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 9.81 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 2.50 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 42.91 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 37.40 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 3.60. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.25. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our washout is 0.00 deg. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root= 0.00 deg, tip= 0.00 deg) Oswalds efficiency is therefore 0.9896 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= 2.477 sqr mtrs, MAC= 9.13 mtrs, incidence= 0.00 deg. Element # 1: S= 2.317 sqr mtrs, MAC= 8.54 mtrs, incidence= 0.00 deg. Element # 2: S= 2.158 sqr mtrs, MAC= 7.96 mtrs, incidence= 0.00 deg. Element # 3: S= 1.999 sqr mtrs, MAC= 7.37 mtrs, incidence= 0.00 deg. init wing side_S=8.95 semilen joined=2.41, sweep25=63.20, side_S=8.95, AR=0.50 After any wing-joining, our semi-length is 2.41 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 9.42 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 7.07 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 68.36 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 63.20 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 0.50. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.75. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our washout is 0.00 deg. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root= 0.00 deg, tip= 0.00 deg) Oswalds efficiency is therefore 0.9773 Finite-Wing & Element Build-Up for VERT STAB 2: root lo Re: NACA 0012 (symmetrical).afl. root hi Re: NACA 0012 (symmetrical).afl. tip lo Re: NACA 0009 (symmetrical).afl. tip hi Re: NACA 0009 (symmetrical).afl. Element # 0: S= 11.757 sqr mtrs, MAC= 11.59 mtrs, incidence= 0.00 deg. Element # 1: S= 10.949 sqr mtrs, MAC= 10.79 mtrs, incidence= 0.00 deg. Element # 2: S= 10.141 sqr mtrs, MAC= 10.00 mtrs, incidence= 0.00 deg. Element # 3: S= 9.334 sqr mtrs, MAC= 9.20 mtrs, incidence= 0.00 deg. Element # 4: S= 8.526 sqr mtrs, MAC= 8.41 mtrs, incidence= 0.00 deg. Element # 5: S= 7.719 sqr mtrs, MAC= 7.61 mtrs, incidence= 0.00 deg. Element # 6: S= 6.911 sqr mtrs, MAC= 6.82 mtrs, incidence= 0.00 deg. Element # 7: S= 6.103 sqr mtrs, MAC= 6.02 mtrs, incidence= 0.00 deg. Element # 8: S= 5.296 sqr mtrs, MAC= 5.23 mtrs, incidence= 0.00 deg. Element # 9: S= 4.488 sqr mtrs, MAC= 4.43 mtrs, incidence= 0.00 deg. init wing side_S=81.22 semilen joined=14.33, sweep25=44.90, side_S=81.22, AR=2.54 After any wing-joining, our semi-length is 14.33 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 11.98 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 4.02 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 50.02 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 44.90 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 2.54. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.34. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our washout is 0.00 deg. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root= 0.00 deg, tip= 0.00 deg) Oswalds efficiency is therefore 0.9826 Finite-Wing & Element Build-Up for MISC WING 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= 0.060 sqr mtrs, MAC= 0.24 mtrs, incidence= 0.00 deg. Element # 1: S= 0.040 sqr mtrs, MAC= 0.16 mtrs, incidence= 0.00 deg. init wing side_S=0.10 semilen joined=0.61, sweep25=34.00, side_S=0.10, AR=5.10 After any wing-joining, our semi-length is 0.61 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 0.27 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 0.12 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 36.87 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 34.00 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 5.10. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.44. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our washout is 0.00 deg. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root= 0.00 deg, tip= 0.00 deg) Oswalds efficiency is therefore 0.9841 Finite-Wing & Element Build-Up for MISC WING 2: 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= 0.057 sqr mtrs, MAC= 0.24 mtrs, incidence= 0.00 deg. Element # 1: S= 0.038 sqr mtrs, MAC= 0.16 mtrs, incidence= 0.00 deg. init wing side_S=0.10 semilen joined=0.58, sweep25=34.00, side_S=0.10, AR=4.85 After any wing-joining, our semi-length is 0.58 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 0.27 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 0.12 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 37.01 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 34.00 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 4.85. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.44. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our washout is 0.00 deg. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root= 0.00 deg, tip= 0.00 deg) Oswalds efficiency is therefore 0.9843 Finite-Wing & Element Build-Up for MISC WING 3: 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= 0.027 sqr mtrs, MAC= 0.28 mtrs, incidence= 0.00 deg. Element # 1: S= 0.021 sqr mtrs, MAC= 0.21 mtrs, incidence= 0.00 deg. init wing side_S=0.05 semilen joined=0.30, sweep25=50.00, side_S=0.05, AR=1.61 After any wing-joining, our semi-length is 0.30 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 0.30 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 0.18 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 53.42 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 50.00 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 1.61. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.60. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our washout is 0.00 deg. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root= 0.00 deg, tip= 0.00 deg) Oswalds efficiency is therefore 0.9748 Finite-Wing & Element Build-Up for MISC WING 5: 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= 0.045 sqr mtrs, MAC= 0.28 mtrs, incidence= 0.00 deg. Element # 1: S= 0.035 sqr mtrs, MAC= 0.21 mtrs, incidence= 0.00 deg. init wing side_S=0.08 semilen joined=0.49, sweep25=48.00, side_S=0.08, AR=2.68 After any wing-joining, our semi-length is 0.49 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 0.30 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 0.18 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 50.29 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 48.00 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 2.68. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.60. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our washout is 0.00 deg. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root= 0.00 deg, tip= 0.00 deg) Oswalds efficiency is therefore 0.9658 Finite-Wing & Element Build-Up for MISC WING 6: 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= 0.032 sqr mtrs, MAC= 0.28 mtrs, incidence= 0.00 deg. Element # 1: S= 0.025 sqr mtrs, MAC= 0.21 mtrs, incidence= 0.00 deg. init wing side_S=0.06 semilen joined=0.37, sweep25=50.00, side_S=0.06, AR=1.93 After any wing-joining, our semi-length is 0.37 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 0.30 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 0.18 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 52.88 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 50.00 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 1.93. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.60. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our washout is 0.00 deg. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root= 0.00 deg, tip= 0.00 deg) Oswalds efficiency is therefore 0.9713 Finite-Wing & Element Build-Up for MISC WING 7: 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= 2.494 sqr mtrs, MAC= 2.58 mtrs, incidence= 0.00 deg. Element # 1: S= 1.663 sqr mtrs, MAC= 1.74 mtrs, incidence= 0.00 deg. init wing side_S=4.16 semilen joined=3.11, sweep25=51.20, side_S=4.16, AR=1.83 After any wing-joining, our semi-length is 3.11 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 2.99 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 1.28 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 55.64 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 51.20 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 1.83. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.43. (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 0.9778 Finite-Wing & Element Build-Up for MISC WING 8: 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= 2.494 sqr mtrs, MAC= 2.58 mtrs, incidence= 0.00 deg. Element # 1: S= 1.663 sqr mtrs, MAC= 1.74 mtrs, incidence= 0.00 deg. init wing side_S=4.16 semilen joined=3.11, sweep25=51.20, side_S=4.16, AR=1.83 After any wing-joining, our semi-length is 3.11 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 2.99 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 1.28 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 55.64 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 51.20 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 1.83. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.43. (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 0.9778 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= 7.302 sqr mtrs, MAC= 6.70 mtrs, incidence= 0.00 deg. init wing side_S=7.30 semilen joined=4.51, sweep25=75.80, side_S=7.30, AR=0.50 Applying biplane interference factor to Oswalds Efficiency! between ENG PYLN 1a and ENG PYLN 2a. This takes e from 0.98 to 0.50. After any wing-joining, our semi-length is 4.51 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 7.99 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 5.21 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 77.68 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 75.80 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 0.50. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.65. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our washout is 0.00 deg. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root= 0.00 deg, tip= 0.00 deg) Oswalds efficiency is therefore 0.5000 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= 7.302 sqr mtrs, MAC= 6.70 mtrs, incidence= 0.00 deg. init wing side_S=7.30 semilen joined=4.51, sweep25=75.80, side_S=7.30, AR=0.50 Applying biplane interference factor to Oswalds Efficiency! between ENG PYLN 2a and ENG PYLN 1a. This takes e from 0.98 to 0.50. After any wing-joining, our semi-length is 4.51 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 7.99 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 5.21 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 77.68 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 75.80 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 0.50. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.65. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our washout is 0.00 deg. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root= 0.00 deg, tip= 0.00 deg) Oswalds efficiency is therefore 0.5000 Finite-Wing & Element Build-Up for ENG PYLN 3a: 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= 7.302 sqr mtrs, MAC= 6.70 mtrs, incidence= 0.00 deg. init wing side_S=7.30 semilen joined=4.51, sweep25=75.80, side_S=7.30, AR=0.50 Applying biplane interference factor to Oswalds Efficiency! between ENG PYLN 3a and ENG PYLN 4a. This takes e from 0.98 to 0.50. After any wing-joining, our semi-length is 4.51 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 7.99 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 5.21 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 77.68 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 75.80 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 0.50. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.65. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our washout is 0.00 deg. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root= 0.00 deg, tip= 0.00 deg) Oswalds efficiency is therefore 0.5000 Finite-Wing & Element Build-Up for ENG PYLN 4a: 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= 7.302 sqr mtrs, MAC= 6.70 mtrs, incidence= 0.00 deg. init wing side_S=7.30 semilen joined=4.51, sweep25=75.80, side_S=7.30, AR=0.50 Applying biplane interference factor to Oswalds Efficiency! between ENG PYLN 4a and ENG PYLN 3a. This takes e from 0.98 to 0.50. After any wing-joining, our semi-length is 4.51 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 7.99 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 5.21 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 77.68 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 75.80 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 0.50. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.65. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our washout is 0.00 deg. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root= 0.00 deg, tip= 0.00 deg) Oswalds efficiency is therefore 0.5000 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 148.626 square meters for all wings listed so far. After RIGT WING 1, the RUNNING TOTAL wetted area is 297.252 square meters for all wings listed so far. After LEFT WING 2, the RUNNING TOTAL wetted area is 314.102 square meters for all wings listed so far. After RIGT WING 2, the RUNNING TOTAL wetted area is 330.953 square meters for all wings listed so far. After LEFT WING 3, the RUNNING TOTAL wetted area is 398.587 square meters for all wings listed so far. After RIGT WING 3, the RUNNING TOTAL wetted area is 466.222 square meters for all wings listed so far. After LEFT WING 4, the RUNNING TOTAL wetted area is 504.744 square meters for all wings listed so far. After RIGT WING 4, the RUNNING TOTAL wetted area is 543.266 square meters for all wings listed so far. After LEFT H STAB, the RUNNING TOTAL wetted area is 611.546 square meters for all wings listed so far. After RIGT H STAB, the RUNNING TOTAL wetted area is 679.826 square meters for all wings listed so far. After VERT STAB 1, the RUNNING TOTAL wetted area is 688.777 square meters for all wings listed so far. After VERT STAB 2, the RUNNING TOTAL wetted area is 770.001 square meters for all wings listed so far. After MISC WING 1, the RUNNING TOTAL wetted area is 770.101 square meters for all wings listed so far. After MISC WING 2, the RUNNING TOTAL wetted area is 770.196 square meters for all wings listed so far. After MISC WING 3, the RUNNING TOTAL wetted area is 770.244 square meters for all wings listed so far. After MISC WING 5, the RUNNING TOTAL wetted area is 770.323 square meters for all wings listed so far. After MISC WING 6, the RUNNING TOTAL wetted area is 770.381 square meters for all wings listed so far. After MISC WING 7, the RUNNING TOTAL wetted area is 774.537 square meters for all wings listed so far. After MISC WING 8, the RUNNING TOTAL wetted area is 778.693 square meters for all wings listed so far. After ENG PYLN 1a, the RUNNING TOTAL wetted area is 785.996 square meters for all wings listed so far. After ENG PYLN 2a, the RUNNING TOTAL wetted area is 793.298 square meters for all wings listed so far. After ENG PYLN 3a, the RUNNING TOTAL wetted area is 800.600 square meters for all wings listed so far. After ENG PYLN 4a, the RUNNING TOTAL wetted area is 807.903 square meters for all wings listed so far. Now for MI from FUSELAGE: The frontal area is 38.451 square meters. The side area is 422.078 square meters. The top area is 370.666 square meters. The RUNNING TOTAL wetted area is 2065.379 square meters, for the entire craft, including all wings, top and bottom surfaces, and all bodies listed so far. The longitudinal centroid is 2.773 meters. The lateral centroid is 0.000 meters. The vertical centroid is 1.121 meters. The radius of gyration in roll is 6.39 meters. The radius of gyration in pitch is 16.21 meters. The radius of gyration in yaw is 17.06 meters. Now for MI from MISC BODY 1: The frontal area is 29.832 square meters. The side area is 135.500 square meters. The top area is 172.690 square meters. The RUNNING TOTAL wetted area is 2593.876 square meters, for the entire craft, including all wings, top and bottom surfaces, and all bodies listed so far. The longitudinal centroid is 0.189 meters. The lateral centroid is 0.000 meters. The vertical centroid is -0.589 meters. The radius of gyration in roll is 5.84 meters. The radius of gyration in pitch is 14.90 meters. The radius of gyration in yaw is 15.65 meters. Now for MI from MISC BODY 2: The frontal area is 0.407 square meters. The side area is 0.598 square meters. The top area is 0.791 square meters. The RUNNING TOTAL wetted area is 2597.293 square meters, for the entire craft, including all wings, top and bottom surfaces, and all bodies listed so far. The longitudinal centroid is -20.626 meters. The lateral centroid is 0.000 meters. The vertical centroid is -1.836 meters. The radius of gyration in roll is 5.84 meters. The radius of gyration in pitch is 14.91 meters. The radius of gyration in yaw is 15.66 meters. Now for MI from MISC BODY 3: The frontal area is 0.056 square meters. The side area is 0.067 square meters. The top area is 0.181 square meters. The RUNNING TOTAL wetted area is 2598.133 square meters, for the entire craft, including all wings, top and bottom surfaces, and all bodies listed so far. The longitudinal centroid is -20.319 meters. The lateral centroid is 0.000 meters. The vertical centroid is -1.874 meters. The radius of gyration in roll is 5.84 meters. The radius of gyration in pitch is 14.91 meters. The radius of gyration in yaw is 15.66 meters. Now for MI from MISC BODY 4: The frontal area is 0.104 square meters. The side area is 0.100 square meters. The top area is 0.269 square meters. The RUNNING TOTAL wetted area is 2598.861 square meters, for the entire craft, including all wings, top and bottom surfaces, and all bodies listed so far. The longitudinal centroid is 2.266 meters. The lateral centroid is 0.000 meters. The vertical centroid is 4.141 meters. The radius of gyration in roll is 5.84 meters. The radius of gyration in pitch is 14.91 meters. The radius of gyration in yaw is 15.66 meters. Now for MI from MISC BODY 5: The frontal area is 0.104 square meters. The side area is 0.100 square meters. The top area is 0.269 square meters. The RUNNING TOTAL wetted area is 2599.588 square meters, for the entire craft, including all wings, top and bottom surfaces, and all bodies listed so far. The longitudinal centroid is 3.150 meters. The lateral centroid is 0.000 meters. The vertical centroid is 4.141 meters. The radius of gyration in roll is 5.84 meters. The radius of gyration in pitch is 14.91 meters. The radius of gyration in yaw is 15.65 meters. Now for MI from MISC BODY 6: The frontal area is 0.120 square meters. The side area is 0.903 square meters. The top area is 1.124 square meters. The RUNNING TOTAL wetted area is 2603.566 square meters, for the entire craft, including all wings, top and bottom surfaces, and all bodies listed so far. The longitudinal centroid is 3.480 meters. The lateral centroid is 5.188 meters. The vertical centroid is -1.601 meters. The radius of gyration in roll is 5.83 meters. The radius of gyration in pitch is 14.90 meters. The radius of gyration in yaw is 15.64 meters. Now for MI from MISC BODY 7: The frontal area is 0.120 square meters. The side area is 0.903 square meters. The top area is 1.124 square meters. The RUNNING TOTAL wetted area is 2607.543 square meters, for the entire craft, including all wings, top and bottom surfaces, and all bodies listed so far. The longitudinal centroid is 3.480 meters. The lateral centroid is -5.188 meters. The vertical centroid is -1.601 meters. The radius of gyration in roll is 5.83 meters. The radius of gyration in pitch is 14.89 meters. The radius of gyration in yaw is 15.63 meters. Now for MI from MISC BODY 8: The frontal area is 0.015 square meters. The side area is 0.118 square meters. The top area is 0.115 square meters. The RUNNING TOTAL wetted area is 2607.913 square meters, for the entire craft, including all wings, top and bottom surfaces, and all bodies listed so far. The longitudinal centroid is 17.762 meters. The lateral centroid is -28.529 meters. The vertical centroid is 1.586 meters. The radius of gyration in roll is 5.84 meters. The radius of gyration in pitch is 14.89 meters. The radius of gyration in yaw is 15.64 meters. Now for MI from MISC BODY 9: The frontal area is 0.015 square meters. The side area is 0.118 square meters. The top area is 0.115 square meters. The RUNNING TOTAL wetted area is 2608.282 square meters, for the entire craft, including all wings, top and bottom surfaces, and all bodies listed so far. The longitudinal centroid is 17.762 meters. The lateral centroid is 28.529 meters. The vertical centroid is 1.586 meters. The radius of gyration in roll is 5.85 meters. The radius of gyration in pitch is 14.89 meters. The radius of gyration in yaw is 15.64 meters. Now for MI from MISC BODY 10: The frontal area is 0.344 square meters. The side area is 0.460 square meters. The top area is 0.870 square meters. The RUNNING TOTAL wetted area is 2611.748 square meters, for the entire craft, including all wings, top and bottom surfaces, and all bodies listed so far. The longitudinal centroid is 38.670 meters. The lateral centroid is 0.000 meters. The vertical centroid is 3.065 meters. The radius of gyration in roll is 5.85 meters. The radius of gyration in pitch is 14.94 meters. The radius of gyration in yaw is 15.70 meters. Now for MI from MISC BODY 11: The frontal area is 0.007 square meters. The side area is 0.115 square meters. The top area is 0.114 square meters. The RUNNING TOTAL wetted area is 2612.128 square meters, for the entire craft, including all wings, top and bottom surfaces, and all bodies listed so far. The longitudinal centroid is -20.914 meters. The lateral centroid is -0.671 meters. The vertical centroid is -1.796 meters. The radius of gyration in roll is 5.85 meters. The radius of gyration in pitch is 14.94 meters. The radius of gyration in yaw is 15.70 meters. Now for MI from MISC BODY 12: The frontal area is 0.007 square meters. The side area is 0.115 square meters. The top area is 0.114 square meters. The RUNNING TOTAL wetted area is 2612.508 square meters, for the entire craft, including all wings, top and bottom surfaces, and all bodies listed so far. The longitudinal centroid is -20.914 meters. The lateral centroid is 0.671 meters. The vertical centroid is -1.796 meters. The radius of gyration in roll is 5.85 meters. The radius of gyration in pitch is 14.95 meters. The radius of gyration in yaw is 15.70 meters. Now for MI from MISC BODY 13: The frontal area is 0.129 square meters. The side area is 0.409 square meters. The top area is 0.653 square meters. The RUNNING TOTAL wetted area is 2614.454 square meters, for the entire craft, including all wings, top and bottom surfaces, and all bodies listed so far. The longitudinal centroid is 10.335 meters. The lateral centroid is 0.000 meters. The vertical centroid is 4.152 meters. The radius of gyration in roll is 5.85 meters. The radius of gyration in pitch is 14.94 meters. The radius of gyration in yaw is 15.69 meters. Now for MI from MISC BODY 17: The frontal area is 3.095 square meters. The side area is 1.575 square meters. The top area is 1.591 square meters. The RUNNING TOTAL wetted area is 2620.456 square meters, for the entire craft, including all wings, top and bottom surfaces, and all bodies listed so far. The longitudinal centroid is -28.639 meters. The lateral centroid is 0.000 meters. The vertical centroid is 0.782 meters. The radius of gyration in roll is 5.84 meters. The radius of gyration in pitch is 14.99 meters. The radius of gyration in yaw is 15.74 meters. Now for MI from MISC BODY 18: The frontal area is 0.016 square meters. The side area is 0.040 square meters. The top area is 0.038 square meters. The RUNNING TOTAL wetted area is 2620.599 square meters, for the entire craft, including all wings, top and bottom surfaces, and all bodies listed so far. The longitudinal centroid is -15.817 meters. The lateral centroid is 0.000 meters. The vertical centroid is 5.138 meters. The radius of gyration in roll is 5.84 meters. The radius of gyration in pitch is 14.99 meters. The radius of gyration in yaw is 15.74 meters. Now for MI from MISC BODY 19: The frontal area is 0.004 square meters. The side area is 0.015 square meters. The top area is 0.023 square meters. The RUNNING TOTAL wetted area is 2620.663 square meters, for the entire craft, including all wings, top and bottom surfaces, and all bodies listed so far. The longitudinal centroid is -20.116 meters. The lateral centroid is 0.000 meters. The vertical centroid is 5.135 meters. The radius of gyration in roll is 5.84 meters. The radius of gyration in pitch is 14.99 meters. The radius of gyration in yaw is 15.74 meters. Now for MI from NACELLE 1: The frontal area is 7.464 square meters. The side area is 20.010 square meters. The top area is 23.548 square meters. The RUNNING TOTAL wetted area is 2705.039 square meters, for the entire craft, including all wings, top and bottom surfaces, and all bodies listed so far. The longitudinal centroid is 5.284 meters. The lateral centroid is -21.062 meters. The vertical centroid is -1.513 meters. The radius of gyration in roll is 6.79 meters. The radius of gyration in pitch is 14.79 meters. The radius of gyration in yaw is 15.93 meters. Now for MI from NACELLE 2: The frontal area is 7.464 square meters. The side area is 20.010 square meters. The top area is 23.548 square meters. The RUNNING TOTAL wetted area is 2789.415 square meters, for the entire craft, including all wings, top and bottom surfaces, and all bodies listed so far. The longitudinal centroid is -3.799 meters. The lateral centroid is -11.918 meters. The vertical centroid is -2.397 meters. The radius of gyration in roll is 6.98 meters. The radius of gyration in pitch is 14.59 meters. The radius of gyration in yaw is 15.83 meters. Now for MI from NACELLE 3: The frontal area is 7.464 square meters. The side area is 20.010 square meters. The top area is 23.548 square meters. The RUNNING TOTAL wetted area is 2873.792 square meters, for the entire craft, including all wings, top and bottom surfaces, and all bodies listed so far. The longitudinal centroid is -3.799 meters. The lateral centroid is 11.918 meters. The vertical centroid is -2.397 meters. The radius of gyration in roll is 7.22 meters. The radius of gyration in pitch is 14.40 meters. The radius of gyration in yaw is 15.76 meters. Now for MI from NACELLE 4: The frontal area is 7.464 square meters. The side area is 20.010 square meters. The top area is 23.548 square meters. The RUNNING TOTAL wetted area is 2958.168 square meters, for the entire craft, including all wings, top and bottom surfaces, and all bodies listed so far. The longitudinal centroid is 5.284 meters. The lateral centroid is 21.062 meters. The vertical centroid is -1.513 meters. The radius of gyration in roll is 8.02 meters. The radius of gyration in pitch is 14.23 meters. The radius of gyration in yaw is 15.99 meters. Now for MI from W-FAIRING 1: The frontal area is 0.112 square meters. The side area is 0.121 square meters. The top area is 0.325 square meters. The RUNNING TOTAL wetted area is 2959.654 square meters, for the entire craft, including all wings, top and bottom surfaces, and all bodies listed so far. The longitudinal centroid is -21.689 meters. The lateral centroid is 0.000 meters. The vertical centroid is -4.137 meters. The radius of gyration in roll is 8.02 meters. The radius of gyration in pitch is 14.23 meters. The radius of gyration in yaw is 15.99 meters. Now for MI from W-FAIRING 2: The frontal area is 0.071 square meters. The side area is 0.378 square meters. The top area is 0.517 square meters. The RUNNING TOTAL wetted area is 2961.561 square meters, for the entire craft, including all wings, top and bottom surfaces, and all bodies listed so far. The longitudinal centroid is 5.470 meters. The lateral centroid is 1.887 meters. The vertical centroid is -4.230 meters. The radius of gyration in roll is 8.01 meters. The radius of gyration in pitch is 14.23 meters. The radius of gyration in yaw is 15.99 meters. Now for MI from W-FAIRING 3: The frontal area is 0.071 square meters. The side area is 0.378 square meters. The top area is 0.517 square meters. The RUNNING TOTAL wetted area is 2963.469 square meters, for the entire craft, including all wings, top and bottom surfaces, and all bodies listed so far. The longitudinal centroid is 5.470 meters. The lateral centroid is -1.887 meters. The vertical centroid is -4.230 meters. The radius of gyration in roll is 8.01 meters. The radius of gyration in pitch is 14.22 meters. The radius of gyration in yaw is 15.98 meters. Now for MI from W-FAIRING 4: The frontal area is 0.071 square meters. The side area is 0.378 square meters. The top area is 0.517 square meters. The RUNNING TOTAL wetted area is 2965.377 square meters, for the entire craft, including all wings, top and bottom surfaces, and all bodies listed so far. The longitudinal centroid is 2.381 meters. The lateral centroid is 5.188 meters. The vertical centroid is -4.233 meters. The radius of gyration in roll is 8.01 meters. The radius of gyration in pitch is 14.22 meters. The radius of gyration in yaw is 15.98 meters. Now for MI from W-FAIRING 5: The frontal area is 0.071 square meters. The side area is 0.378 square meters. The top area is 0.517 square meters. The RUNNING TOTAL wetted area is 2967.284 square meters, for the entire craft, including all wings, top and bottom surfaces, and all bodies listed so far. The longitudinal centroid is 2.381 meters. The lateral centroid is -5.188 meters. The vertical centroid is -4.233 meters. The radius of gyration in roll is 8.01 meters. The radius of gyration in pitch is 14.22 meters. The radius of gyration in yaw is 15.97 meters. Engines have mass 20672.93 kg (11.56% of total): The radius of gyration of the engines in roll is 17.23 m, based on all engine powers/thrusts and locations. The radius of gyration of the engines in pitch is 6.74 m, based on all engine powers/thrusts and locations. The radius of gyration of the engines in yaw is 18.28 m, based on all engine powers/thrusts and locations. Remainder of the craft has mass 158082.42 (88.44% of total): The radius of gyration of the shell in roll is 8.01 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 14.22 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 15.97 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 9.54 m. The radius of gyration in pitch is 13.56 m. The radius of gyration in yaw is 16.26 m. For LEFT WING 1: Full slat #1 deployment will cause coefficient data to spread out alpha-wise to 150.00% 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 150.00% 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 150.00% 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 150.00% 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 3: Full slat #1 deployment will cause coefficient data to spread out alpha-wise to 150.00% 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 3: Full slat #1 deployment will cause coefficient data to spread out alpha-wise to 150.00% 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 4: Full slat #1 deployment will cause coefficient data to spread out alpha-wise to 150.00% 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 4: Full slat #1 deployment will cause coefficient data to spread out alpha-wise to 150.00% 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 9.70 m (positive aft from CG) when the 25% chord is assumed to be the element location. The centroid of all foils is at 10.22 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 7.22 m. So you could say the static margin is 1.34 (positive stable) when the 25% chord is assumed to be the element location. So you could say the static margin is 1.42 (positive stable) when the wing is looked at partially as a delta-wing based on taper ratio.