Stuart Buchanan Ron Jensen 2002-01-01 Cessna C-182RG 174 35.8 4.9 21.9 15.7 16.5 0 43.2 0 59.4 37 0 48 43.9 0 40.6 948 1346 1967 1700 41 0 36.5 180 36 -14 24 -6.8 0 -20 0.8 0.5 0.02 1800 600 20 NONE 1 58.2 -43 -15.5 0.8 0.5 0.02 5400 1600 0.0 LEFT 1 58.2 43 -15.5 0.8 0.5 0.02 5400 1600 0.0 RIGHT 1 -15.0 0.0 -10.0 0.2 0.2 0.2 10000 2000 188 0 8 0.2 0.2 0.2 20000 1000 43.2 -214.8 59.4 0.2 0.2 0.2 10000 2000 43.2 214.8 59.4 0.2 0.2 0.2 10000 2000 -19.7 0 26.6 0.0 0 0 0 1 -37.7 0 26.6 0.0 0.0 0.0 1 10 56 -112 59.4 300 200 56 112 59.4 300 200 fcs/elevator-cmd-norm fcs/pitch-trim-cmd-norm -1 1 fcs/pitch-trim-sum 0.01745 -28 23

fcs/elevator-pos-rad

fcs/elevator-pos-deg -25 35 -1 1

fcs/elevator-pos-norm

fcs/aileron-cmd-norm fcs/roll-trim-cmd-norm -1 1 fcs/roll-trim-sum 0.01745 -20 15

fcs/left-aileron-pos-rad

fcs/left-aileron-pos-deg -20 15 -0.75 1

fcs/left-aileron-pos-norm

fcs/right-aileron-pos-deg -20 15 -0.75 1

fcs/right-aileron-pos-norm

fcs/rudder-cmd-norm fcs/yaw-trim-cmd-norm -1 1 fcs/yaw-trim-sum 0.01745 -16 16

fcs/rudder-pos-rad

fcs/rudder-pos-deg -25 25 -1 1

fcs/rudder-pos-norm

fcs/flap-cmd-norm 0 0 10 2 20 1 30 1

fcs/flap-pos-deg

fcs/flap-pos-deg 0 30 0 1

fcs/flap-pos-norm

gear/gear-cmd-norm 0 0 1 5

gear/gear-pos-norm

Change in lift due to ground effect. aero/h_b-mac-ft 0.0000 1.2030 0.1000 1.1270 0.1500 1.0900 0.2000 1.0730 0.3000 1.0460 0.4000 1.0550 0.5000 1.0190 0.6000 1.0130 0.7000 1.0080 0.8000 1.0060 0.9000 1.0030 1.0000 1.0020 1.1000 1.0000 Coefficient of lift at zero alpha. aero/function/kCLge 0.3070 Coefficient of lift due to alpha. aero/function/kCLge aero/alpha-rad -0.0900 -0.5270 0.0000 -0.0570 0.1400 0.7130 0.2100 0.9450 0.2400 1.0470 0.2600 1.1330 0.2800 1.1590 0.3000 1.1250 0.3200 1.0740 0.3400 0.9910 0.3600 0.6630 Coefficient of lift due to flap deflection. aero/function/kCLge fcs/flap-pos-deg 0.0000 0.0000 10.0000 0.2000 20.0000 0.3000 30.0000 0.3500 Coefficient of lift due to alpha rate. aero/alphadot-rad_sec aero/ci2vel 1.7000 Coefficient of lift due to pitch rate. velocities/q-aero-rad_sec aero/ci2vel 3.9000 Coefficient of lift due to elevator deflection. fcs/elevator-pos-rad 0.21 Total coefficient of lift. aero/coefficient/CLo aero/coefficient/CLalpha aero/coefficient/CLDf aero/coefficient/CLadot aero/coefficient/CLq aero/coefficient/CLDe Force of lift, total. Just for debugging; not used anywhere. aero/qbar-psf metrics/Sw-sqft aero/coefficient/CL Force of drag at zero lift. aero/qbar-psf metrics/Sw-sqft 0.015 Force of drag (induced) due to alpha. aero/qbar-psf metrics/Sw-sqft aero/coefficient/CL aero/coefficient/CL 0.065 Force of drag (parasite) due to alpha. Large when alpha is beyond critical. 0 Force of drag due to slip. aero/qbar-psf metrics/Sw-sqft aero/beta-rad aero/beta-rad 1.500 Force of drag due to flap deflection. aero/qbar-psf metrics/Sw-sqft aero/alpha-radfcs/flap-pos-deg 0.0000 10.0000 20.0000 30.0000 -0.0873 0.0000 0.0030 0.0084 0.0153 -0.0698 0.0000 0.0061 0.0131 0.0208 -0.0524 0.0000 0.0092 0.0178 0.0263 -0.0349 0.0000 0.0124 0.0225 0.0317 -0.0175 0.0000 0.0155 0.0272 0.0372 0.0000 0.0000 0.0186 0.0319 0.0427 0.0175 0.0000 0.0218 0.0367 0.0483 0.0349 0.0000 0.0250 0.0415 0.0539 0.0524 0.0000 0.0282 0.0463 0.0594 0.0698 0.0000 0.0314 0.0511 0.0650 0.0873 0.0000 0.0346 0.0558 0.0706 0.1047 0.0000 0.0378 0.0606 0.0762 0.1222 0.0000 0.0409 0.0654 0.0818 0.1396 0.0000 0.0441 0.0702 0.0873 0.1571 0.0000 0.0461 0.0731 0.0907 0.1745 0.0000 0.0480 0.0760 0.0941 0.1920 0.0000 0.0499 0.0789 0.0975 0.2094 0.0000 0.0518 0.0818 0.1008 0.2269 0.0000 0.0538 0.0847 0.1043 0.2443 0.0000 0.0559 0.0879 0.1080 0.2618 0.0000 0.0582 0.0913 0.1120 0.2793 0.0000 0.0590 0.0925 0.1133 0.2967 0.0000 0.0581 0.0911 0.1117 0.3142 0.0000 0.0567 0.0890 0.1093 0.3316 0.0000 0.0546 0.0859 0.1056 0.3491 0.0000 0.0485 0.0767 0.0950 Force of drag due to gear. aero/qbar-psf metrics/Sw-sqft .01 gear/gear-pos-norm 0.0 0.0 0.1 1.0 0.5 1.5 1.0 1.0 Force of drag due to Elevator Deflection. Effect is small. aero/qbar-psf metrics/Sw-sqft fcs/mag-elevator-pos-rad 0.0000 Side Force due to slip (beta) (per radian). Makes boat turn possible. Contributes to damping of Dutch Roll mode. aero/qbar-psf metrics/Sw-sqft aero/beta-rad -0.5 Side force due to roll rate. aero/qbar-psf metrics/Sw-sqft aero/bi2vel velocities/p-aero-rad_sec aero/alpha-rad 0.0000 -0.0750 0.0943 -0.1450 Side force due to yaw rate. aero/qbar-psf metrics/Sw-sqft aero/bi2vel velocities/r-aero-rad_sec aero/alpha-rad 0.0000 0.2140 0.0943 0.2670 Side force due to aileron. aero/qbar-psf metrics/Sw-sqft fcs/left-aileron-pos-rad 0.0000 Side force due to rudder. aero/qbar-psf metrics/Sw-sqft fcs/rudder-pos-rad 0.1870 Force of lift at zero alpha. aero/qbar-psf metrics/Sw-sqft aero/coefficient/CLo Force of lift due to alpha. aero/qbar-psf metrics/Sw-sqft aero/coefficient/CLalpha Force of lift due to flap deflection. aero/qbar-psf metrics/Sw-sqft aero/coefficient/CLDf Force of lift due to alpha rate. aero/qbar-psf metrics/Sw-sqft aero/coefficient/CLadot Force of lift due to pitch rate. aero/qbar-psf metrics/Sw-sqft aero/coefficient/CLq Force of lift due to elevator deflection. aero/qbar-psf metrics/Sw-sqft aero/coefficient/CLDe Roll Moment due to slip (beta) (per radian). Decrease of Mlb to small negative value improves Dutch Roll Damping. High Positive value leads to excessive spiral instability. aero/qbar-psf metrics/Sw-sqft metrics/bw-ft 0.3 aero/beta-radaero/alpha-rad 0.0000 0.0943 -0.3490 0.0322 0.0312 0.0000 0.0000 0.0000 0.3490 -0.0322 -0.0312 Roll moment due to roll rate. Canonical contribution to roll damping. aero/qbar-psf metrics/Sw-sqft metrics/bw-ft aero/bi2vel velocities/p-aero-rad_sec aero/alpha-rad 0.0000 -0.4840 0.0943 -0.4870 0.3000 0.0 Roll moment due to yaw rate. aero/qbar-psf metrics/Sw-sqft metrics/bw-ft aero/bi2vel velocities/r-aero-rad_sec aero/alpha-rad 0.0000 0.0798 0.0943 0.1869 Roll moment due to aileron deflection. aero/qbar-psf metrics/Sw-sqft metrics/bw-ft fcs/left-aileron-pos-rad 0.10 Roll moment due to engine thrust. (E.g. asymmetric incidence of wing roots.) aero/qbar-psf metrics/Sw-sqft metrics/bw-ft propulsion/engine/thrust_lb 0.000006 Roll moment due to rudder. aero/qbar-psf metrics/Sw-sqft metrics/bw-ft fcs/rudder-pos-rad -0.0147 Pitching moment at zero alpha. aero/qbar-psf metrics/Sw-sqft metrics/cbarw-ft 0.00 Pitch moment due to alpha. Includes major contribution from decalage. aero/qbar-psf metrics/Sw-sqft metrics/cbarw-ft aero/alpha-rad -0.6 Pitch moment due to alpha rate. aero/qbar-psf metrics/Sw-sqft metrics/cbarw-ft aero/ci2vel aero/alphadot-rad_sec aero/alpha-rad 0.0000 -7.2700 0.0943 -5.5700 Pitch moment due to pitch rate. aero/qbar-psf metrics/Sw-sqft metrics/cbarw-ft aero/ci2vel velocities/q-aero-rad_sec -6.0 Pitch moment due to flaps. Primarily to compensate for Mmalpha * change in incidence. aero/qbar-psf metrics/Sw-sqft metrics/cbarw-ft fcs/flap-pos-deg 0.0033 -0.6 Pitch moment due to flaps * thrust. aero/qbar-psf metrics/Sw-sqft metrics/cbarw-ft propulsion/engine/thrust_lb .00001 Pitch moment due to elevator deflection. aero/qbar-psf metrics/Sw-sqft metrics/cbarw-ft fcs/elevator-pos-rad aero/alpha-rad 0.0000 -0.31 0.0943 -0.43 Yaw moment due to slip (beta) (per radian) Determines Dutch Roll and Spiral characteristics. Prevents side-slip and yawing moments. aero/qbar-psf metrics/Sw-sqft metrics/bw-ft aero/beta-rad aero/alpha-rad 0.0000 0.0587 0.0943 0.0907 Yaw moment due to roll rate (per radian) Reduces Dutch Roll damping. Positive value desirable. aero/qbar-psf metrics/Sw-sqft metrics/bw-ft aero/bi2vel velocities/p-aero-rad_sec aero/alpha-rad 0.0000 -0.0278 0.0943 -0.0649 Yaw Moment due to yaw rate (per radian) Aka yaw damping. Main contributor to damping of Dutch Roll. aero/qbar-psf metrics/Sw-sqft metrics/bw-ft aero/bi2vel velocities/r-aero-rad_sec -0.3 Yaw moment due to aileron. One of the big contributors to adverse yaw. aero/qbar-psf metrics/Sw-sqft metrics/bw-ft fcs/left-aileron-pos-rad aero/alpha-rad -0.2000 0.0500 0.0500 0.0000 0.3000 -0.0500 Yaw moment due to rudder. aero/qbar-psf metrics/Sw-sqft metrics/bw-ft fcs/rudder-pos-rad aero/alpha-rad 0.0000 -0.0645 0.0943 -0.0805