•••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••• X-Plane, by Austin Meyer Simulating Aircraft/General Aviation/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= 0.016 sqr mtrs, MAC= 0.17 mtrs, incidence= 77.83 deg. Element # 1: S= 0.015 sqr mtrs, MAC= 0.17 mtrs, incidence= 57.09 deg. Element # 2: S= 0.015 sqr mtrs, MAC= 0.16 mtrs, incidence= 42.83 deg. Element # 3: S= 0.014 sqr mtrs, MAC= 0.15 mtrs, incidence= 33.51 deg. Element # 4: S= 0.013 sqr mtrs, MAC= 0.14 mtrs, incidence= 27.25 deg. Element # 5: S= 0.012 sqr mtrs, MAC= 0.14 mtrs, incidence= 22.85 deg. Element # 6: S= 0.012 sqr mtrs, MAC= 0.13 mtrs, incidence= 19.62 deg. Element # 7: S= 0.011 sqr mtrs, MAC= 0.12 mtrs, incidence= 17.17 deg. Element # 8: S= 0.010 sqr mtrs, MAC= 0.11 mtrs, incidence= 15.25 deg. Element # 9: S= 0.010 sqr mtrs, MAC= 0.11 mtrs, incidence= 13.71 deg. init wing side_S=0.13 semilen joined=0.91, sweep25=0.00, side_S=0.13, AR=13.09 After any wing-joining, our semi-length is 0.91 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our root chord is 0.18 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our tip chord is 0.10 mtrs. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our leading-edge sweep is 1.19 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 13.09. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.57. (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= 77.83 deg, tip= 13.71 deg) Oswalds efficiency is therefore 0.9863 Finite-Wing & Element Build-Up for LEFT WING 1: root lo Re: NACA 2412.afl. root hi Re: NACA 2412.afl. tip lo Re: NACA 2412.afl. tip hi Re: NACA 2412.afl. Element # 0: S= 0.749 sqr mtrs, MAC= 1.58 mtrs, incidence= 3.00 deg. Element # 1: S= 0.749 sqr mtrs, MAC= 1.58 mtrs, incidence= 3.00 deg. Element # 2: S= 0.749 sqr mtrs, MAC= 1.58 mtrs, incidence= 3.00 deg. Element # 3: S= 0.749 sqr mtrs, MAC= 1.58 mtrs, incidence= 3.00 deg. Element # 4: S= 0.749 sqr mtrs, MAC= 1.58 mtrs, incidence= 3.00 deg. init wing side_S=3.74 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=7.87) semilen joined=6.00, sweep25=1.28, side_S=7.87, AR=9.14 After any wing-joining, our semi-length is 6.00 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 2.45 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 1.28 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 9.14. (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 4.00 deg. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root= 3.00 deg, tip= -1.00 deg) Oswalds efficiency is therefore 0.9887 Finite-Wing & Element Build-Up for RIGT WING 1: root lo Re: NACA 2412.afl. root hi Re: NACA 2412.afl. tip lo Re: NACA 2412.afl. tip hi Re: NACA 2412.afl. Element # 0: S= 0.749 sqr mtrs, MAC= 1.58 mtrs, incidence= 3.00 deg. Element # 1: S= 0.749 sqr mtrs, MAC= 1.58 mtrs, incidence= 3.00 deg. Element # 2: S= 0.749 sqr mtrs, MAC= 1.58 mtrs, incidence= 3.00 deg. Element # 3: S= 0.749 sqr mtrs, MAC= 1.58 mtrs, incidence= 3.00 deg. Element # 4: S= 0.749 sqr mtrs, MAC= 1.58 mtrs, incidence= 3.00 deg. init wing side_S=3.74 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=7.87) semilen joined=6.00, sweep25=1.28, side_S=7.87, AR=9.14 After any wing-joining, our semi-length is 6.00 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 2.45 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 1.28 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 9.14. (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 4.00 deg. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root= 3.00 deg, tip= -1.00 deg) Oswalds efficiency is therefore 0.9887 Finite-Wing & Element Build-Up for LEFT WING 2: root lo Re: NACA 2412.afl. root hi Re: NACA 2412.afl. tip lo Re: NACA 2412.afl. tip hi Re: NACA 2412.afl. Element # 0: S= 0.681 sqr mtrs, MAC= 1.55 mtrs, incidence= 3.00 deg. Element # 1: S= 0.650 sqr mtrs, MAC= 1.48 mtrs, incidence= 3.00 deg. Element # 2: S= 0.620 sqr mtrs, MAC= 1.41 mtrs, incidence= 3.00 deg. Element # 3: S= 0.589 sqr mtrs, MAC= 1.34 mtrs, incidence= 2.50 deg. Element # 4: S= 0.559 sqr mtrs, MAC= 1.27 mtrs, incidence= 1.20 deg. Element # 5: S= 0.528 sqr mtrs, MAC= 1.20 mtrs, incidence= 0.00 deg. Element # 6: S= 0.497 sqr mtrs, MAC= 1.13 mtrs, incidence= -1.00 deg. init wing side_S=4.12 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=7.87) semilen joined=6.00, sweep25=1.28, side_S=7.87, AR=9.14 After any wing-joining, our semi-length is 6.00 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 2.45 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 1.28 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 9.14. (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 4.00 deg. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root= 3.00 deg, tip= -1.00 deg) Oswalds efficiency is therefore 0.9887 Finite-Wing & Element Build-Up for RIGT WING 2: root lo Re: NACA 2412.afl. root hi Re: NACA 2412.afl. tip lo Re: NACA 2412.afl. tip hi Re: NACA 2412.afl. Element # 0: S= 0.681 sqr mtrs, MAC= 1.55 mtrs, incidence= 3.00 deg. Element # 1: S= 0.650 sqr mtrs, MAC= 1.48 mtrs, incidence= 3.00 deg. Element # 2: S= 0.620 sqr mtrs, MAC= 1.41 mtrs, incidence= 3.00 deg. Element # 3: S= 0.589 sqr mtrs, MAC= 1.34 mtrs, incidence= 2.50 deg. Element # 4: S= 0.559 sqr mtrs, MAC= 1.27 mtrs, incidence= 1.20 deg. Element # 5: S= 0.528 sqr mtrs, MAC= 1.20 mtrs, incidence= 0.00 deg. Element # 6: S= 0.497 sqr mtrs, MAC= 1.13 mtrs, incidence= -1.00 deg. init wing side_S=4.12 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=7.87) semilen joined=6.00, sweep25=1.28, side_S=7.87, AR=9.14 After any wing-joining, our semi-length is 6.00 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 2.45 deg. (for purposes of Delta-Wing factor determination only) After any wing-joining, our mean aero sweep is 1.28 deg. (for purposes of Oswalds Efficiency determination only) After any wing-joining, our aspect ratio is 9.14. (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 4.00 deg. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root= 3.00 deg, tip= -1.00 deg) Oswalds efficiency is therefore 0.9887 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= 0.319 sqr mtrs, MAC= 1.19 mtrs, incidence= 1.50 deg. Element # 1: S= 0.302 sqr mtrs, MAC= 1.13 mtrs, incidence= 1.50 deg. Element # 2: S= 0.286 sqr mtrs, MAC= 1.07 mtrs, incidence= 1.50 deg. Element # 3: S= 0.270 sqr mtrs, MAC= 1.01 mtrs, incidence= 0.50 deg. Element # 4: S= 0.253 sqr mtrs, MAC= 0.95 mtrs, incidence= 0.50 deg. Element # 5: S= 0.237 sqr mtrs, MAC= 0.88 mtrs, incidence= 0.50 deg. init wing side_S=1.67 semilen joined=1.71, sweep25=4.73, side_S=1.67, AR=3.47 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 1.22 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 7.78 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 3.47. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.70. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our washout is 1.00 deg. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root= 1.50 deg, tip= 0.50 deg) Oswalds efficiency is therefore 0.9893 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= 0.319 sqr mtrs, MAC= 1.19 mtrs, incidence= 1.50 deg. Element # 1: S= 0.302 sqr mtrs, MAC= 1.13 mtrs, incidence= 1.50 deg. Element # 2: S= 0.286 sqr mtrs, MAC= 1.07 mtrs, incidence= 1.50 deg. Element # 3: S= 0.270 sqr mtrs, MAC= 1.01 mtrs, incidence= 0.50 deg. Element # 4: S= 0.253 sqr mtrs, MAC= 0.95 mtrs, incidence= 0.50 deg. Element # 5: S= 0.237 sqr mtrs, MAC= 0.88 mtrs, incidence= 0.50 deg. init wing side_S=1.67 semilen joined=1.71, sweep25=4.73, side_S=1.67, AR=3.47 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 1.22 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 7.78 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 3.47. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our taper ratio is 0.70. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only) After any wing-joining, our washout is 1.00 deg. (for purposes of Oswalds Efficiency and Delta-Wing factor determination only, root= 1.50 deg, tip= 0.50 deg) Oswalds efficiency is therefore 0.9893 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. init wing side_S=2.15 semilen joined=2.15, sweep25=38.00, side_S=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 The PROPELLER 1 DISC AREA is broken down into rings for propwash distribution as follows: element number 0, rad1= 0.00, rad2= 0.09, ring area= 0.026 square meters. element number 1, rad1= 0.09, rad2= 0.18, ring area= 0.079 square meters. element number 2, rad1= 0.18, rad2= 0.27, ring area= 0.131 square meters. element number 3, rad1= 0.27, rad2= 0.37, ring area= 0.184 square meters. element number 4, rad1= 0.37, rad2= 0.46, ring area= 0.236 square meters. element number 5, rad1= 0.46, rad2= 0.55, ring area= 0.289 square meters. element number 6, rad1= 0.55, rad2= 0.64, ring area= 0.341 square meters. element number 7, rad1= 0.64, rad2= 0.73, ring area= 0.394 square meters. element number 8, rad1= 0.73, rad2= 0.82, ring area= 0.447 square meters. element number 9, rad1= 0.82, rad2= 0.91, ring area= 0.499 square meters. TOTAL DISC AREA= 2.627 square meters. Before any tip weights, the PROPELLER 1 weighs 12.30 kg, and the MI is 4.35 kg*m*m. The SEMI-SPAN of the blades is 0.91 m, and the moment of inertia in rotation about the HUB (for RPM change) is 4.35 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 3.744 square meters for all wings listed so far. After RIGT WING 1, the RUNNING TOTAL wetted area is 7.488 square meters for all wings listed so far. After LEFT WING 2, the RUNNING TOTAL wetted area is 11.613 square meters for all wings listed so far. After RIGT WING 2, the RUNNING TOTAL wetted area is 15.737 square meters for all wings listed so far. After LEFT H STAB, the RUNNING TOTAL wetted area is 17.405 square meters for all wings listed so far. After RIGT H STAB, the RUNNING TOTAL wetted area is 19.073 square meters for all wings listed so far. After VERT STAB 1, the RUNNING TOTAL wetted area is 21.228 square meters for all wings listed so far. Now for MI from FUSELAGE: The frontal area is 1.710 square meters. The side area is 6.950 square meters. The top area is 6.102 square meters. The RUNNING TOTAL wetted area is 44.927 square meters, for the entire craft, including all wings, top and bottom surfaces, and all bodies listed so far. The longitudinal centroid is 0.848 meters. The lateral centroid is 0.000 meters. The vertical centroid is -0.095 meters. The radius of gyration in roll is 1.60 meters. The radius of gyration in pitch is 1.91 meters. The radius of gyration in yaw is 2.41 meters. Now for MI from NACELLE 1: The frontal area is 0.089 square meters. The side area is 0.076 square meters. The top area is 0.074 square meters. The RUNNING TOTAL wetted area is 45.268 square meters, for the entire craft, including all wings, top and bottom surfaces, and all bodies listed so far. The longitudinal centroid is -2.206 meters. The lateral centroid is 0.000 meters. The vertical centroid is -0.123 meters. The radius of gyration in roll is 1.60 meters. The radius of gyration in pitch is 1.92 meters. The radius of gyration in yaw is 2.41 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 RUNNING TOTAL wetted area is 45.918 square meters, for the entire craft, including all wings, top and bottom surfaces, and all bodies listed so far. The longitudinal centroid is -1.230 meters. The lateral centroid is 0.000 meters. The vertical centroid is -1.197 meters. The radius of gyration in roll is 1.59 meters. The radius of gyration in pitch is 1.91 meters. The radius of gyration in yaw is 2.39 meters. Now for MI from W-FAIRING 2: The frontal area is 0.075 square meters. The side area is 0.254 square meters. The top area is 0.161 square meters. The RUNNING TOTAL wetted area is 46.652 square meters, for the entire craft, including all wings, top and bottom surfaces, and all bodies listed so far. The longitudinal centroid is 0.608 meters. The lateral centroid is -1.201 meters. The vertical centroid is -1.094 meters. The radius of gyration in roll is 1.59 meters. The radius of gyration in pitch is 1.91 meters. The radius of gyration in yaw is 2.38 meters. Now for MI from W-FAIRING 3: The frontal area is 0.075 square meters. The side area is 0.254 square meters. The top area is 0.161 square meters. The RUNNING TOTAL wetted area is 47.387 square meters, for the entire craft, including all wings, top and bottom surfaces, and all bodies listed so far. The longitudinal centroid is 0.608 meters. The lateral centroid is 1.201 meters. The vertical centroid is -1.094 meters. The radius of gyration in roll is 1.59 meters. The radius of gyration in pitch is 1.90 meters. The radius of gyration in yaw is 2.37 meters. Engines have mass 143.03 kg (18.32% of total): The radius of gyration of the engines in roll is 0.12 m, based on all engine powers/thrusts and locations. The radius of gyration of the engines in pitch is 2.23 m, based on all engine powers/thrusts and locations. The radius of gyration of the engines in yaw is 2.23 m, based on all engine powers/thrusts and locations. Remainder of the craft has mass 637.61 (81.68% of total): The radius of gyration of the shell in roll is 1.59 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 1.90 m, based on mass-distribution across the shell of the craft with a 50% weighting on all of the flying surfaces. The radius of gyration of the shell in yaw is 2.37 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 1.44 m. The radius of gyration in pitch is 1.96 m. The radius of gyration in yaw is 2.34 m. The centroid of all foils is at 1.31 m (positive aft from CG) when the 25% chord is assumed to be the element location. The centroid of all foils is at 1.32 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 1.30 m. So you could say the static margin is 1.00 (positive stable) when the 25% chord is assumed to be the element location. So you could say the static margin is 1.01 (positive stable) when the wing is looked at partially as a delta-wing based on taper ratio.