•••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••• X-Plane, by Austin Meyer Simulating Aircraft/General Aviation/Alabeo C207_Skywagon_v3.2/C207_Skywagon.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: NACA_16_Prop_INT.afl. root hi Re: NACA_16_Prop_INT.afl. tip lo Re: NACA 16 Prop.afl. tip hi Re: NACA 16 Prop.afl. Element # 0: S= 0.013 sqr mtrs, MAC= 0.13 mtrs, incidence= 62.39 deg. Element # 1: S= 0.012 sqr mtrs, MAC= 0.12 mtrs, incidence= 46.33 deg. Element # 2: S= 0.012 sqr mtrs, MAC= 0.12 mtrs, incidence= 33.52 deg. Element # 3: S= 0.011 sqr mtrs, MAC= 0.11 mtrs, incidence= 23.97 deg. Element # 4: S= 0.011 sqr mtrs, MAC= 0.11 mtrs, incidence= 16.93 deg. Element # 5: S= 0.010 sqr mtrs, MAC= 0.10 mtrs, incidence= 11.68 deg. Element # 6: S= 0.010 sqr mtrs, MAC= 0.10 mtrs, incidence= 7.67 deg. Element # 7: S= 0.009 sqr mtrs, MAC= 0.09 mtrs, incidence= 4.53 deg. Element # 8: S= 0.009 sqr mtrs, MAC= 0.09 mtrs, incidence= 2.03 deg. Element # 9: S= 0.008 sqr mtrs, MAC= 0.08 mtrs, incidence= 0.00 deg. init wing side_S=0.11 semilen joined=0.99, sweep25=0.00, side_S=0.11, AR=18.57 After any wing-joining, our semi-length is 0.99 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 0.13 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 0.73 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 18.57. (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= 62.39 deg, tip= 0.00 deg) Oswalds efficiency is therefore 0.9721 Finite-Wing & Element Build-Up for LEFT WING 1: root lo Re: NACA 65(216)-415(lam flow)3m.afl. root hi Re: NACA 65(216)-415(lam flow)9m.afl. tip lo Re: NACA 65(216)-415(lam flow)3m.afl. tip hi Re: NACA 65(216)-415(lam flow)9m.afl. Element # 0: S= 0.827 sqr mtrs, MAC= 1.57 mtrs, incidence= 2.50 deg. Element # 1: S= 0.842 sqr mtrs, MAC= 1.60 mtrs, incidence= 2.10 deg. Element # 2: S= 0.842 sqr mtrs, MAC= 1.60 mtrs, incidence= 1.70 deg. Element # 3: S= 0.840 sqr mtrs, MAC= 1.59 mtrs, incidence= 1.20 deg. Element # 4: S= 0.827 sqr mtrs, MAC= 1.57 mtrs, incidence= 0.80 deg. Element # 5: S= 0.787 sqr mtrs, MAC= 1.49 mtrs, incidence= 0.40 deg. Element # 6: S= 0.725 sqr mtrs, MAC= 1.38 mtrs, incidence= 0.00 deg. Element # 7: S= 0.675 sqr mtrs, MAC= 1.28 mtrs, incidence= -0.30 deg. Element # 8: S= 0.630 sqr mtrs, MAC= 1.20 mtrs, incidence= -0.80 deg. Element # 9: S= 0.577 sqr mtrs, MAC= 1.10 mtrs, incidence= -1.20 deg. init wing side_S=7.57 semilen joined=5.48, sweep25=-0.55, side_S=7.57, AR=7.94 After any wing-joining, our semi-length is 5.48 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 1.40 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 1.16 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 0.09 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is -0.55 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 7.94. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.83. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our washout is 3.70 deg. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root= 2.50 deg, tip= -1.20 deg) Oswalds efficiency is therefore 0.9909 Finite-Wing & Element Build-Up for RIGT WING 1: root lo Re: NACA 65(216)-415(lam flow)3m.afl. root hi Re: NACA 65(216)-415(lam flow)9m.afl. tip lo Re: NACA 65(216)-415(lam flow)3m.afl. tip hi Re: NACA 65(216)-415(lam flow)9m.afl. Element # 0: S= 0.827 sqr mtrs, MAC= 1.57 mtrs, incidence= 2.50 deg. Element # 1: S= 0.842 sqr mtrs, MAC= 1.60 mtrs, incidence= 2.10 deg. Element # 2: S= 0.842 sqr mtrs, MAC= 1.60 mtrs, incidence= 1.70 deg. Element # 3: S= 0.840 sqr mtrs, MAC= 1.59 mtrs, incidence= 1.20 deg. Element # 4: S= 0.827 sqr mtrs, MAC= 1.57 mtrs, incidence= 0.80 deg. Element # 5: S= 0.787 sqr mtrs, MAC= 1.49 mtrs, incidence= 0.40 deg. Element # 6: S= 0.725 sqr mtrs, MAC= 1.38 mtrs, incidence= 0.00 deg. Element # 7: S= 0.675 sqr mtrs, MAC= 1.28 mtrs, incidence= -0.30 deg. Element # 8: S= 0.630 sqr mtrs, MAC= 1.20 mtrs, incidence= -0.80 deg. Element # 9: S= 0.577 sqr mtrs, MAC= 1.10 mtrs, incidence= -1.20 deg. init wing side_S=7.57 semilen joined=5.48, sweep25=-0.55, side_S=7.57, AR=7.94 After any wing-joining, our semi-length is 5.48 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 1.40 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 1.16 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 0.09 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is -0.55 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 7.94. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.83. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our washout is 3.70 deg. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root= 2.50 deg, tip= -1.20 deg) Oswalds efficiency is therefore 0.9909 Finite-Wing & Element Build-Up for LEFT H STAB: root lo Re: NACA 0012 (symmetrical).afl. root hi Re: NACA 0012 (symmetrical).afl. tip lo Re: NACA 0012 (symmetrical).afl. tip hi Re: NACA 0012 (symmetrical).afl. Element # 0: S= 0.426 sqr mtrs, MAC= 1.09 mtrs, incidence= 0.30 deg. Element # 1: S= 0.483 sqr mtrs, MAC= 1.22 mtrs, incidence= 0.30 deg. Element # 2: S= 0.439 sqr mtrs, MAC= 1.11 mtrs, incidence= 0.30 deg. Element # 3: S= 0.391 sqr mtrs, MAC= 0.99 mtrs, incidence= 0.30 deg. Element # 4: S= 0.340 sqr mtrs, MAC= 0.86 mtrs, incidence= 0.30 deg. init wing side_S=2.08 semilen joined=2.00, sweep25=6.90, side_S=2.08, AR=3.77 After any wing-joining, our semi-length is 2.00 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 1.46 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 0.91 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 10.77 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 6.90 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 3.77. (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= 0.30 deg, tip= 0.30 deg) Oswalds efficiency is therefore 0.9881 Finite-Wing & Element Build-Up for RIGT H STAB: root lo Re: NACA 0012 (symmetrical).afl. root hi Re: NACA 0012 (symmetrical).afl. tip lo Re: NACA 0012 (symmetrical).afl. tip hi Re: NACA 0012 (symmetrical).afl. Element # 0: S= 0.426 sqr mtrs, MAC= 1.09 mtrs, incidence= 0.30 deg. Element # 1: S= 0.483 sqr mtrs, MAC= 1.22 mtrs, incidence= 0.30 deg. Element # 2: S= 0.439 sqr mtrs, MAC= 1.11 mtrs, incidence= 0.30 deg. Element # 3: S= 0.391 sqr mtrs, MAC= 0.99 mtrs, incidence= 0.30 deg. Element # 4: S= 0.340 sqr mtrs, MAC= 0.86 mtrs, incidence= 0.30 deg. init wing side_S=2.08 semilen joined=2.00, sweep25=6.90, side_S=2.08, AR=3.77 After any wing-joining, our semi-length is 2.00 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 1.46 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 0.91 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 10.77 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 6.90 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 3.77. (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= 0.30 deg, tip= 0.30 deg) Oswalds efficiency is therefore 0.9881 Finite-Wing & Element Build-Up for VERT STAB 1: 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= 0.123 sqr mtrs, MAC= 1.35 mtrs, incidence= 0.00 deg. Element # 1: S= 0.097 sqr mtrs, MAC= 1.07 mtrs, incidence= 0.00 deg. Element # 2: S= 0.070 sqr mtrs, MAC= 0.78 mtrs, incidence= 0.00 deg. Element # 3: S= 0.044 sqr mtrs, MAC= 0.49 mtrs, incidence= 0.00 deg. init wing side_S=0.33 semilen joined=1.07, sweep25=70.00, side_S=0.33, AR=0.80 After any wing-joining, our semi-length is 1.07 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 1.49 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 0.34 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 74.23 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 70.00 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 0.80. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.22. (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 0.9845 Finite-Wing & Element Build-Up for VERT STAB 2: 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= 0.492 sqr mtrs, MAC= 1.29 mtrs, incidence= 0.00 deg. Element # 1: S= 0.425 sqr mtrs, MAC= 1.11 mtrs, incidence= 0.00 deg. Element # 2: S= 0.358 sqr mtrs, MAC= 0.94 mtrs, incidence= 0.00 deg. Element # 3: S= 0.291 sqr mtrs, MAC= 0.76 mtrs, incidence= 0.00 deg. init wing side_S=1.57 semilen joined=1.92, sweep25=37.00, side_S=1.57, AR=3.00 After any wing-joining, our semi-length is 1.92 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 0.67 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 40.95 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 37.00 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 3.00. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.49. (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 0.9811 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= 0.031 square meters. element number 1, rad1= 0.10, rad2= 0.20, ring area= 0.092 square meters. element number 2, rad1= 0.20, rad2= 0.30, ring area= 0.154 square meters. element number 3, rad1= 0.30, rad2= 0.40, ring area= 0.216 square meters. element number 4, rad1= 0.40, rad2= 0.50, ring area= 0.277 square meters. element number 5, rad1= 0.50, rad2= 0.59, ring area= 0.339 square meters. element number 6, rad1= 0.59, rad2= 0.69, ring area= 0.401 square meters. element number 7, rad1= 0.69, rad2= 0.79, ring area= 0.462 square meters. element number 8, rad1= 0.79, rad2= 0.89, ring area= 0.524 square meters. element number 9, rad1= 0.89, rad2= 0.99, ring area= 0.586 square meters. TOTAL DISC AREA= 3.083 square meters. Before any tip weights, the PROPELLER 1 weighs 12.69 kg, and the MI is 5.26 kg*m*m. The SEMI-SPAN of the blades is 0.99 m, and the moment of inertia in rotation about the HUB (for RPM change) is 5.26 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 7.570 square meters for all wings listed so far. After RIGT WING 1, the RUNNING TOTAL wetted area is 15.141 square meters for all wings listed so far. After LEFT H STAB, the RUNNING TOTAL wetted area is 17.220 square meters for all wings listed so far. After RIGT H STAB, the RUNNING TOTAL wetted area is 19.300 square meters for all wings listed so far. After VERT STAB 1, the RUNNING TOTAL wetted area is 19.634 square meters for all wings listed so far. After VERT STAB 2, the RUNNING TOTAL wetted area is 21.200 square meters for all wings listed so far. Now for MI from FUSELAGE: The frontal area is 1.356 square meters. The side area is 7.683 square meters. The top area is 6.244 square meters. The RUNNING TOTAL wetted area is 45.119 square meters, for the entire craft, including all wings, top and bottom surfaces, and all bodies listed so far. The longitudinal centroid is 0.886 meters. The lateral centroid is 0.000 meters. The vertical centroid is 0.043 meters. The radius of gyration in roll is 1.41 meters. The radius of gyration in pitch is 2.11 meters. The radius of gyration in yaw is 2.46 meters. Engines have mass 269.22 kg (31.40% of total): The radius of gyration of the engines in roll is 0.02 m, based on all engine powers/thrusts and locations. The radius of gyration of the engines in pitch is 2.73 m, based on all engine powers/thrusts and locations. The radius of gyration of the engines in yaw is 2.73 m, based on all engine powers/thrusts and locations. Remainder of the craft has mass 588.07 (68.60% of total): The radius of gyration of the shell in roll is 1.41 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 2.11 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 2.46 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 1.17 m. The radius of gyration in pitch is 2.32 m. The radius of gyration in yaw is 2.55 m. The centroid of all foils is at 1.20 m (positive aft from CG) when the 25% chord is assumed to be the element location. The centroid of all foils is at 1.21 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 1.24 m. So you could say the static margin is 0.97 (positive stable) when the 25% chord is assumed to be the element location.