•••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••• X-Plane, by Austin Meyer Simulating Aircraft/Laminar Research/Cessna 172SP/Cessna_172SP.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 PROPELLER 1: root lo Re: Clark-Y (root).afl root hi Re: Clark-Y (root).afl tip lo Re: Clark-Y (good propeller).afl tip hi Re: Clark-Y (good propeller).afl Element # 0: S= 0.015 sqr mtrs, MAC= 0.15 mtrs, incidence= 77.41 deg Element # 1: S= 0.014 sqr mtrs, MAC= 0.14 mtrs, incidence= 56.17 deg Element # 2: S= 0.013 sqr mtrs, MAC= 0.13 mtrs, incidence= 41.84 deg Element # 3: S= 0.013 sqr mtrs, MAC= 0.13 mtrs, incidence= 32.60 deg Element # 4: S= 0.012 sqr mtrs, MAC= 0.12 mtrs, incidence= 26.45 deg Element # 5: S= 0.011 sqr mtrs, MAC= 0.11 mtrs, incidence= 22.15 deg Element # 6: S= 0.010 sqr mtrs, MAC= 0.10 mtrs, incidence= 19.00 deg Element # 7: S= 0.010 sqr mtrs, MAC= 0.10 mtrs, incidence= 16.62 deg Element # 8: S= 0.009 sqr mtrs, MAC= 0.09 mtrs, incidence= 14.75 deg Element # 9: S= 0.008 sqr mtrs, MAC= 0.08 mtrs, incidence= 13.26 deg Wing area for this wing=0.11 When joined to other wings, we have semi-length=1.01, sweep25=0.00, area=0.11, AR=17.60 After any wing-joining, our semi-length is 1.01 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 0.15 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 0.08 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 1.09 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 0.00 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 17.60. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.50. (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= 77.41 deg, tip= 13.26 deg) Oswalds efficiency is therefore 0.9849 Finite-Wing & Element Build-Up for LEFT WING 1: root lo Re: NACA 2412-root.afl root hi Re: NACA 2412-root.afl tip lo Re: NACA 2412-root.afl tip hi Re: NACA 2412-root.afl Element # 0: S= 0.338 sqr mtrs, MAC= 1.58 mtrs, incidence= 3.00 deg Element # 1: S= 0.338 sqr mtrs, MAC= 1.58 mtrs, incidence= 3.00 deg Element # 2: S= 0.338 sqr mtrs, MAC= 1.58 mtrs, incidence= 3.00 deg Element # 3: S= 0.338 sqr mtrs, MAC= 1.58 mtrs, incidence= 3.00 deg Element # 4: S= 0.338 sqr mtrs, MAC= 1.58 mtrs, incidence= 3.00 deg Element # 5: S= 0.338 sqr mtrs, MAC= 1.58 mtrs, incidence= 3.00 deg Element # 6: S= 0.338 sqr mtrs, MAC= 1.58 mtrs, incidence= 3.00 deg Element # 7: S= 0.338 sqr mtrs, MAC= 1.58 mtrs, incidence= 3.00 deg Element # 8: S= 0.338 sqr mtrs, MAC= 1.58 mtrs, incidence= 3.00 deg Element # 9: S= 0.338 sqr mtrs, MAC= 1.58 mtrs, incidence= 3.00 deg Wing area for this wing=3.38 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=7.26) When joined to other wings, we have semi-length=5.52, sweep25=1.31, area=7.26, AR=8.37 Applying biplane interference factor to Oswalds Efficiency! between LEFT WING 1 and LEFT WING 3. This takes e from 0.99 to 0.59 After any wing-joining, our semi-length is 5.52 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 1.58 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 1.10 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 2.58 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 1.31 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 8.37. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.69. (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 0.5889 Finite-Wing & Element Build-Up for RIGT WING 1: root lo Re: NACA 2412-root.afl root hi Re: NACA 2412-root.afl tip lo Re: NACA 2412-root.afl tip hi Re: NACA 2412-root.afl Element # 0: S= 0.338 sqr mtrs, MAC= 1.58 mtrs, incidence= 3.00 deg Element # 1: S= 0.338 sqr mtrs, MAC= 1.58 mtrs, incidence= 3.00 deg Element # 2: S= 0.338 sqr mtrs, MAC= 1.58 mtrs, incidence= 3.00 deg Element # 3: S= 0.338 sqr mtrs, MAC= 1.58 mtrs, incidence= 3.00 deg Element # 4: S= 0.338 sqr mtrs, MAC= 1.58 mtrs, incidence= 3.00 deg Element # 5: S= 0.338 sqr mtrs, MAC= 1.58 mtrs, incidence= 3.00 deg Element # 6: S= 0.338 sqr mtrs, MAC= 1.58 mtrs, incidence= 3.00 deg Element # 7: S= 0.338 sqr mtrs, MAC= 1.58 mtrs, incidence= 3.00 deg Element # 8: S= 0.338 sqr mtrs, MAC= 1.58 mtrs, incidence= 3.00 deg Element # 9: S= 0.338 sqr mtrs, MAC= 1.58 mtrs, incidence= 3.00 deg Wing area for this wing=3.38 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=7.26) When joined to other wings, we have semi-length=5.52, sweep25=1.31, area=7.26, AR=8.37 Applying biplane interference factor to Oswalds Efficiency! between RIGT WING 1 and RIGT WING 3. This takes e from 0.99 to 0.59 After any wing-joining, our semi-length is 5.52 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 1.58 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 1.10 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 2.58 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 1.31 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 8.37. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.69. (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 0.5889 Finite-Wing & Element Build-Up for LEFT WING 2: root lo Re: NACA 2412-root.afl root hi Re: NACA 2412-root.afl tip lo Re: NACA 2412-tip.afl tip hi Re: NACA 2412-tip.afl Element # 0: S= 0.451 sqr mtrs, MAC= 1.56 mtrs, incidence= 3.00 deg Element # 1: S= 0.437 sqr mtrs, MAC= 1.51 mtrs, incidence= 3.00 deg Element # 2: S= 0.423 sqr mtrs, MAC= 1.46 mtrs, incidence= 3.00 deg Element # 3: S= 0.409 sqr mtrs, MAC= 1.41 mtrs, incidence= 2.50 deg Element # 4: S= 0.395 sqr mtrs, MAC= 1.37 mtrs, incidence= 1.20 deg Element # 5: S= 0.381 sqr mtrs, MAC= 1.32 mtrs, incidence= 0.00 deg Element # 6: S= 0.367 sqr mtrs, MAC= 1.27 mtrs, incidence= -1.00 deg Element # 7: S= 0.353 sqr mtrs, MAC= 1.22 mtrs, incidence= 0.00 deg Element # 8: S= 0.339 sqr mtrs, MAC= 1.17 mtrs, incidence= 0.00 deg Element # 9: S= 0.324 sqr mtrs, MAC= 1.12 mtrs, incidence= 0.00 deg Wing area for this wing=3.88 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=7.26) When joined to other wings, we have semi-length=5.52, sweep25=1.31, area=7.26, AR=8.37 After any wing-joining, our semi-length is 5.52 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 1.58 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 1.10 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 2.58 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 1.31 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 8.37. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.69. (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 0.9919 Finite-Wing & Element Build-Up for RIGT WING 2: root lo Re: NACA 2412-root.afl root hi Re: NACA 2412-root.afl tip lo Re: NACA 2412-tip.afl tip hi Re: NACA 2412-tip.afl Element # 0: S= 0.451 sqr mtrs, MAC= 1.56 mtrs, incidence= 3.00 deg Element # 1: S= 0.437 sqr mtrs, MAC= 1.51 mtrs, incidence= 3.00 deg Element # 2: S= 0.423 sqr mtrs, MAC= 1.46 mtrs, incidence= 3.00 deg Element # 3: S= 0.409 sqr mtrs, MAC= 1.41 mtrs, incidence= 2.50 deg Element # 4: S= 0.395 sqr mtrs, MAC= 1.37 mtrs, incidence= 1.20 deg Element # 5: S= 0.381 sqr mtrs, MAC= 1.32 mtrs, incidence= 0.00 deg Element # 6: S= 0.367 sqr mtrs, MAC= 1.27 mtrs, incidence= -1.00 deg Element # 7: S= 0.353 sqr mtrs, MAC= 1.22 mtrs, incidence= 0.00 deg Element # 8: S= 0.339 sqr mtrs, MAC= 1.17 mtrs, incidence= 0.00 deg Element # 9: S= 0.324 sqr mtrs, MAC= 1.12 mtrs, incidence= 0.00 deg Wing area for this wing=3.88 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=7.26) When joined to other wings, we have semi-length=5.52, sweep25=1.31, area=7.26, AR=8.37 After any wing-joining, our semi-length is 5.52 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 1.58 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 1.10 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 2.58 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 1.31 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 8.37. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.69. (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 0.9919 Finite-Wing & Element Build-Up for LEFT WING 3: root lo Re: NACA 0024 (symmetrical).afl root hi Re: NACA 0024 (symmetrical).afl tip lo Re: NACA 0024 (symmetrical).afl tip hi Re: NACA 0024 (symmetrical).afl Element # 0: S= 0.035 sqr mtrs, MAC= 0.15 mtrs, incidence= 0.00 deg Element # 1: S= 0.035 sqr mtrs, MAC= 0.15 mtrs, incidence= 0.00 deg Element # 2: S= 0.035 sqr mtrs, MAC= 0.15 mtrs, incidence= 0.00 deg Element # 3: S= 0.035 sqr mtrs, MAC= 0.15 mtrs, incidence= 0.00 deg Element # 4: S= 0.035 sqr mtrs, MAC= 0.15 mtrs, incidence= 0.00 deg Element # 5: S= 0.035 sqr mtrs, MAC= 0.15 mtrs, incidence= 0.00 deg Element # 6: S= 0.035 sqr mtrs, MAC= 0.15 mtrs, incidence= 0.00 deg Element # 7: S= 0.035 sqr mtrs, MAC= 0.15 mtrs, incidence= 0.00 deg Element # 8: S= 0.035 sqr mtrs, MAC= 0.15 mtrs, incidence= 0.00 deg Element # 9: S= 0.035 sqr mtrs, MAC= 0.15 mtrs, incidence= 0.00 deg Wing area for this wing=0.35 When joined to other wings, we have semi-length=2.77, sweep25=5.77, area=0.35, AR=43.99 Applying biplane interference factor to Oswalds Efficiency! between LEFT WING 3 and LEFT WING 1. This takes e from 0.83 to 0.59 After any wing-joining, our semi-length is 2.77 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 0.15 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 0.15 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 5.77 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 5.77 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 43.99. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 1.00. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our washout is 0.00 deg. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root= 0.00 deg, tip= 0.00 deg) Oswalds efficiency is therefore 0.5889 Finite-Wing & Element Build-Up for RIGT WING 3: root lo Re: NACA 0024 (symmetrical).afl root hi Re: NACA 0024 (symmetrical).afl tip lo Re: NACA 0024 (symmetrical).afl tip hi Re: NACA 0024 (symmetrical).afl Element # 0: S= 0.035 sqr mtrs, MAC= 0.15 mtrs, incidence= 0.00 deg Element # 1: S= 0.035 sqr mtrs, MAC= 0.15 mtrs, incidence= 0.00 deg Element # 2: S= 0.035 sqr mtrs, MAC= 0.15 mtrs, incidence= 0.00 deg Element # 3: S= 0.035 sqr mtrs, MAC= 0.15 mtrs, incidence= 0.00 deg Element # 4: S= 0.035 sqr mtrs, MAC= 0.15 mtrs, incidence= 0.00 deg Element # 5: S= 0.035 sqr mtrs, MAC= 0.15 mtrs, incidence= 0.00 deg Element # 6: S= 0.035 sqr mtrs, MAC= 0.15 mtrs, incidence= 0.00 deg Element # 7: S= 0.035 sqr mtrs, MAC= 0.15 mtrs, incidence= 0.00 deg Element # 8: S= 0.035 sqr mtrs, MAC= 0.15 mtrs, incidence= 0.00 deg Element # 9: S= 0.035 sqr mtrs, MAC= 0.15 mtrs, incidence= 0.00 deg Wing area for this wing=0.35 When joined to other wings, we have semi-length=2.77, sweep25=5.77, area=0.35, AR=43.99 Applying biplane interference factor to Oswalds Efficiency! between RIGT WING 3 and RIGT WING 1. This takes e from 0.83 to 0.59 After any wing-joining, our semi-length is 2.77 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 0.15 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 0.15 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 5.77 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 5.77 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 43.99. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 1.00. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our washout is 0.00 deg. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root= 0.00 deg, tip= 0.00 deg) Oswalds efficiency is therefore 0.5889 Finite-Wing & Element Build-Up for LEFT H STAB: root lo Re: NACA 0006 (symmetrical).afl root hi Re: NACA 0006 (symmetrical).afl tip lo Re: NACA 0006 (symmetrical).afl tip hi Re: NACA 0006 (symmetrical).afl Element # 0: S= 0.217 sqr mtrs, MAC= 1.35 mtrs, incidence= 0.00 deg Element # 1: S= 0.208 sqr mtrs, MAC= 1.29 mtrs, incidence= 0.00 deg Element # 2: S= 0.200 sqr mtrs, MAC= 1.24 mtrs, incidence= 0.00 deg Element # 3: S= 0.192 sqr mtrs, MAC= 1.19 mtrs, incidence= 0.00 deg Element # 4: S= 0.183 sqr mtrs, MAC= 1.14 mtrs, incidence= 0.00 deg Element # 5: S= 0.175 sqr mtrs, MAC= 1.09 mtrs, incidence= 0.00 deg Element # 6: S= 0.167 sqr mtrs, MAC= 1.04 mtrs, incidence= 0.00 deg Element # 7: S= 0.158 sqr mtrs, MAC= 0.98 mtrs, incidence= 0.00 deg Element # 8: S= 0.150 sqr mtrs, MAC= 0.93 mtrs, incidence= 0.00 deg Element # 9: S= 0.142 sqr mtrs, MAC= 0.88 mtrs, incidence= 0.00 deg Wing area for this wing=1.79 When joined to other wings, we have semi-length=1.71, sweep25=4.73, area=1.79, AR=3.23 After any wing-joining, our semi-length is 1.71 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 1.37 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 0.85 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 9.03 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 4.73 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 3.23. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.62. (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 0.9876 Finite-Wing & Element Build-Up for RIGT H STAB: root lo Re: NACA 0006 (symmetrical).afl root hi Re: NACA 0006 (symmetrical).afl tip lo Re: NACA 0006 (symmetrical).afl tip hi Re: NACA 0006 (symmetrical).afl Element # 0: S= 0.217 sqr mtrs, MAC= 1.35 mtrs, incidence= 0.00 deg Element # 1: S= 0.208 sqr mtrs, MAC= 1.29 mtrs, incidence= 0.00 deg Element # 2: S= 0.200 sqr mtrs, MAC= 1.24 mtrs, incidence= 0.00 deg Element # 3: S= 0.192 sqr mtrs, MAC= 1.19 mtrs, incidence= 0.00 deg Element # 4: S= 0.183 sqr mtrs, MAC= 1.14 mtrs, incidence= 0.00 deg Element # 5: S= 0.175 sqr mtrs, MAC= 1.09 mtrs, incidence= 0.00 deg Element # 6: S= 0.167 sqr mtrs, MAC= 1.04 mtrs, incidence= 0.00 deg Element # 7: S= 0.158 sqr mtrs, MAC= 0.98 mtrs, incidence= 0.00 deg Element # 8: S= 0.150 sqr mtrs, MAC= 0.93 mtrs, incidence= 0.00 deg Element # 9: S= 0.142 sqr mtrs, MAC= 0.88 mtrs, incidence= 0.00 deg Wing area for this wing=1.79 When joined to other wings, we have semi-length=1.71, sweep25=4.73, area=1.79, AR=3.23 After any wing-joining, our semi-length is 1.71 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 1.37 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 0.85 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 9.03 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 4.73 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 3.23. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.62. (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 0.9876 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= 0.372 sqr mtrs, MAC= 1.76 mtrs, incidence= 0.30 deg Element # 1: S= 0.343 sqr mtrs, MAC= 1.62 mtrs, incidence= 0.20 deg Element # 2: S= 0.314 sqr mtrs, MAC= 1.48 mtrs, incidence= 0.10 deg Element # 3: S= 0.284 sqr mtrs, MAC= 1.34 mtrs, incidence= 0.00 deg Element # 4: S= 0.255 sqr mtrs, MAC= 1.20 mtrs, incidence= 0.00 deg Element # 5: S= 0.225 sqr mtrs, MAC= 1.07 mtrs, incidence= 0.00 deg Element # 6: S= 0.196 sqr mtrs, MAC= 0.93 mtrs, incidence= 0.00 deg Element # 7: S= 0.166 sqr mtrs, MAC= 0.79 mtrs, incidence= 0.00 deg Wing area for this wing=2.15 When joined to other wings, we have semi-length=2.15, sweep25=38.00, area=2.15, AR=2.66 After any wing-joining, our semi-length is 2.15 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 1.83 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 0.72 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 43.40 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 38.00 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 2.66. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.39. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our washout is 0.30 deg. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root= 0.30 deg, tip= 0.00 deg) Oswalds efficiency is therefore 0.9847 Finite-Wing & Element Build-Up for VERT STAB 2: root lo Re: Flat Plate (very thin).afl root hi Re: Flat Plate (very thin).afl tip lo Re: NACA 0009 (symmetrical).afl tip hi Re: NACA 0009 (symmetrical).afl Element # 0: S= 0.148 sqr mtrs, MAC= 1.88 mtrs, incidence= 0.00 deg Element # 1: S= 0.106 sqr mtrs, MAC= 1.35 mtrs, incidence= 0.00 deg Element # 2: S= 0.064 sqr mtrs, MAC= 0.83 mtrs, incidence= 0.00 deg Element # 3: S= 0.021 sqr mtrs, MAC= 0.36 mtrs, incidence= 0.00 deg Wing area for this wing=0.34 When joined to other wings, we have semi-length=1.83, sweep25=80.00, area=0.34, AR=0.60 After any wing-joining, our semi-length is 1.83 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 2.13 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 0.00 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 82.25 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 80.00 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 0.60. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.00. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our washout is 0.00 deg. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root= 0.00 deg, tip= 0.00 deg) Oswalds efficiency is therefore 0.9820 The PROPELLER 1 DISC AREA is broken down into rings for propwash distribution as follows: element number 0, rad1= 0.00, rad2= 0.10, ring area= 0.032 square meters element number 1, rad1= 0.10, rad2= 0.20, ring area= 0.095 square meters element number 2, rad1= 0.20, rad2= 0.30, ring area= 0.159 square meters element number 3, rad1= 0.30, rad2= 0.40, ring area= 0.222 square meters element number 4, rad1= 0.40, rad2= 0.50, ring area= 0.286 square meters element number 5, rad1= 0.50, rad2= 0.60, ring area= 0.350 square meters element number 6, rad1= 0.60, rad2= 0.70, ring area= 0.413 square meters element number 7, rad1= 0.70, rad2= 0.80, ring area= 0.477 square meters element number 8, rad1= 0.80, rad2= 0.91, ring area= 0.540 square meters element number 9, rad1= 0.91, rad2= 1.01, ring area= 0.604 square meters TOTAL DISC AREA= 3.178 square meters Before any tip weights, the PROPELLER 1 weighs 9.37 kg, and the MI is 4.00 kg*m*m The SEMI-SPAN of the blades is 1.01 m, and the moment of inertia in rotation about the HUB (for RPM change) is 4.00 kg*m*m Critical altitude=0.00 mtrs, rho at crit alt=1.23 kg/mmm, rho at SL=1.23 kg/mmm, engine power boosted to 1.0000 of original After LEFT WING 1, the RUNNING TOTAL wetted area is 3.382 square meters for all wings listed so far After RIGT WING 1, the RUNNING TOTAL wetted area is 6.763 square meters for all wings listed so far After LEFT WING 2, the RUNNING TOTAL wetted area is 10.643 square meters for all wings listed so far After RIGT WING 2, the RUNNING TOTAL wetted area is 14.523 square meters for all wings listed so far After LEFT WING 3, the RUNNING TOTAL wetted area is 14.868 square meters for all wings listed so far After RIGT WING 3, the RUNNING TOTAL wetted area is 15.214 square meters for all wings listed so far After LEFT H STAB, the RUNNING TOTAL wetted area is 17.005 square meters for all wings listed so far After RIGT H STAB, the RUNNING TOTAL wetted area is 18.795 square meters for all wings listed so far After VERT STAB 1, the RUNNING TOTAL wetted area is 20.950 square meters for all wings listed so far After VERT STAB 2, the RUNNING TOTAL wetted area is 21.289 square meters for all wings listed so far Now for MI from FUSELAGE: The frontal area is 1.716 square meters The side area is 6.573 square meters The top area is 6.061 square meters The longitudinal centroid is 0.80 meters The lateral centroid is 0.00 meters The vertical centroid is -0.10 meters The RUNNING TOTAL wetted area is 44.719 square meters, for the entire craft, including all wings, top and bottom surfaces, and all bodies listed so far The RUNNING TOTAL radius of gyration in roll is 1.43 meters The RUNNING TOTAL radius of gyration in pitch is 1.87 meters The RUNNING TOTAL radius of gyration in yaw is 2.27 meters Now for MI from NACELLE 1: The frontal area is 0.089 square meters The side area is 0.095 square meters The top area is 0.092 square meters The longitudinal centroid is -2.15 meters The lateral centroid is 0.00 meters The vertical centroid is -0.06 meters The RUNNING TOTAL wetted area is 45.114 square meters, for the entire craft, including all wings, top and bottom surfaces, and all bodies listed so far The RUNNING TOTAL radius of gyration in roll is 1.42 meters The RUNNING TOTAL radius of gyration in pitch is 1.88 meters The RUNNING TOTAL radius of gyration in yaw is 2.27 meters Now for MI from W-FAIRING 1: The frontal area is 0.068 square meters The side area is 0.220 square meters The top area is 0.149 square meters The longitudinal centroid is -1.29 meters The lateral centroid is 0.00 meters The vertical centroid is -1.11 meters The RUNNING TOTAL wetted area is 45.764 square meters, for the entire craft, including all wings, top and bottom surfaces, and all bodies listed so far The RUNNING TOTAL radius of gyration in roll is 1.42 meters The RUNNING TOTAL radius of gyration in pitch is 1.88 meters The RUNNING TOTAL radius of gyration in yaw is 2.26 meters Now for MI from W-FAIRING 2: The frontal area is 0.075 square meters The side area is 0.253 square meters The top area is 0.161 square meters The longitudinal centroid is 0.39 meters The lateral centroid is -1.29 meters The vertical centroid is -1.03 meters The RUNNING TOTAL wetted area is 46.498 square meters, for the entire craft, including all wings, top and bottom surfaces, and all bodies listed so far The RUNNING TOTAL radius of gyration in roll is 1.42 meters The RUNNING TOTAL radius of gyration in pitch is 1.87 meters The RUNNING TOTAL radius of gyration in yaw is 2.25 meters Now for MI from W-FAIRING 3: The frontal area is 0.075 square meters The side area is 0.253 square meters The top area is 0.161 square meters The longitudinal cen