-.2793
.4189
Change in lift due to ground effect factor
aero/h_b-mac-ft
0.0 1.203
0.1 1.127
0.15 1.090
0.2 1.073
0.3 1.046
0.4 1.055
0.5 1.019
0.6 1.013
0.7 1.008
0.8 1.006
0.9 1.003
1.0 1.002
1.1 1.0
Change in drag due to ground effect
aero/h_b-mac-ft
0.0 0.480
0.1 0.515
0.15 0.629
0.2 0.709
0.3 0.815
0.4 0.882
0.5 0.928
0.6 0.962
0.7 0.988
0.8 1.0
0.9 1.0
1.0 1.0
1.1 1.0
Lift due to alpha
Increase in CL decreases Period and damping,Dutch Roll damping
CL is low for landing
aero/function/ground-effect-factor-lift
aero/qbar-psf
metrics/Sw-sqft
0.83
aero/alpha-rad
-.2793 -1.205
-.1745 -.5125
-.1396 -.2906
-.1047 -.7663E-01
-.6981E-01 .1375
-.3491E-01 .3586
.000 .5854
.3491E-01 .8176
.6981E-01 1.055
.1396 1.490
.1745 1.654
.2094 1.776
.2443 1.845
.2618 1.837
.2793 1.807
.2967 1.554
.3142 1.203
.3491 .6313
.3840 .1405
.4189 -.2022
Basic Lift Coefficient due to pitch rate(per radian)
velocities/q-aero-rad_sec
aero/qbar-psf
metrics/Sw-sqft
aero/ci2vel
aero/alpha-rad
-.2793 7.488
-.1745 7.488
-.1396 7.488
-.1047 7.488
-.6981E-01 7.488
-.3491E-01 7.488
.000 7.488
.3491E-01 7.488
.6981E-01 7.488
.1396 7.488
.1745 7.488
.2094 7.488
.2443 7.488
.2618 7.488
.2793 7.488
.2967 7.488
.3142 7.488
.3491 7.488
.3840 7.488
.4189 7.488
Basic Lift Coefficient due to AOA rate
Important contributor to Short-Period damping
For low Cla, aircraft must land at high alpha
aero/alphadot-rad_sec
aero/qbar-psf
metrics/Sw-sqft
aero/ci2vel
aero/alpha-rad
-.2793 1.783
-.1745 1.841
-.1396 1.857
-.1047 1.881
-.6981E-01 1.954
-.3491E-01 2.044
.000 2.118
.3491E-01 2.079
.6981E-01 1.933
.1396 1.536
.1745 1.196
.2094 .7401
.2443 .3574
.2618 -.6955
.2793 -1.752
.2967 -3.991
.3142 -5.246
.3491 -3.057
.3840 -2.436
.4189 -2.063
Lift Coefficient due to Left Fowler Flaps Deflection
Positive surface deflection is trailing edge down
Ultimately, we will feed this left flap pos
aero/qbar-psf
metrics/Sw-sqft
fcs/flap-pos-deg
.000 .000
8.000 .2988E-01
12.00 .5975E-01
25.00 .1285
Lift Coefficient due to Right Fowler Flaps Deflection
Positive surface deflection is trailing edge down
Ultimately, we will feed this right flap pos
aero/qbar-psf
metrics/Sw-sqft
fcs/flap-pos-deg
.000 .000
8.000 .2988E-01
12.00 .5975E-01
25.00 .1285
Lift Coefficient due to Elevator Deflection
Positive surface deflection is trailing edge down
aero/qbar-psf
metrics/Sw-sqft
fcs/elevator-pos-rad
-.3491 -.1026
-.2618 -.9847E-01
-.1745 -.7035E-01
-.8727E-01 -.3518E-01
.000 .7035E-04
.8727E-01 .3518E-01
.1745 .7035E-01
.2618 .9847E-01
.3491 .1026
Basic Drag Coefficient
Sense: Always positive
Main contributor to Phugoid damping: Greater Cd, Better damping
aero/function/ground-effect-factor-drag
aero/qbar-psf
metrics/Sw-sqft
1.30
aero/alpha-rad
-.2793 .7340E-01
-.1745 .2602E-01
-.1396 .1883E-01
-.1047 .1537E-01
-.6981E-01 .1568E-01
-.3491E-01 .1983E-01
.000 .2837E-01
.3491E-01 .4131E-01
.6981E-01 .5898E-01
.1396 .1021
.1745 .1211
.2094 .1365
.2443 .1458
.2618 .1429
.2793 .1390
.2967 .1005
.3142 .7088E-01
.3491 .4924E-01
.3840 .4910E-01
.4189 .5829E-01
Drag Coefficient due to Left Fowler Flaps Deflection
Positive surface deflection is trailing edge down
Ultimately, we will feed this left flap pos
aero/qbar-psf
metrics/Sw-sqft
aero/alpha-deg
fcs/flap-pos-deg
.000 8.000 12.00 25.00
-16.00 .000 -.2250E-02 -.4354E-02 -.8641E-02
-10.00 .000 -.1154E-02 -.2163E-02 -.3929E-02
-8.000 .000 -.7889E-03 -.1432E-02 -.2359E-02
-6.000 .000 -.4237E-03 -.7018E-03 -.7887E-03
-4.000 .000 -.5849E-04 .2865E-04 .7817E-03
-2.000 .000 .3067E-03 .7591E-03 .2352E-02
.000 .000 .6719E-03 .1489E-02 .3922E-02
2.000 .000 .1037E-02 .2220E-02 .5493E-02
4.000 .000 .1402E-02 .2950E-02 .7063E-02
8.000 .000 .2133E-02 .4411E-02 .1020E-01
10.00 .000 .2498E-02 .5142E-02 .1177E-01
12.00 .000 .2863E-02 .5872E-02 .1334E-01
14.00 .000 .3228E-02 .6602E-02 .1492E-01
15.00 .000 .3411E-02 .6968E-02 .1570E-01
16.00 .000 .3594E-02 .7333E-02 .1649E-01
17.00 .000 .3776E-02 .7698E-02 .1727E-01
18.00 .000 .3959E-02 .8063E-02 .1806E-01
20.00 .000 .4324E-02 .8794E-02 .1963E-01
22.00 .000 .4689E-02 .9524E-02 .2120E-01
24.00 .000 .5054E-02 .1025E-01 .2277E-01
Drag Coefficient due to Right Fowler Flaps Deflection
Positive surface deflection is trailing edge down
Ultimately, we will feed this right flap pos
aero/qbar-psf
metrics/Sw-sqft
aero/alpha-deg
fcs/flap-pos-deg
.000 8.000 12.00 25.00
-16.00 .000 -.2250E-02 -.4354E-02 -.8641E-02
-10.00 .000 -.1154E-02 -.2163E-02 -.3929E-02
-8.000 .000 -.7889E-03 -.1432E-02 -.2359E-02
-6.000 .000 -.4237E-03 -.7018E-03 -.7887E-03
-4.000 .000 -.5849E-04 .2865E-04 .7817E-03
-2.000 .000 .3067E-03 .7591E-03 .2352E-02
.000 .000 .6719E-03 .1489E-02 .3922E-02
2.000 .000 .1037E-02 .2220E-02 .5493E-02
4.000 .000 .1402E-02 .2950E-02 .7063E-02
8.000 .000 .2133E-02 .4411E-02 .1020E-01
10.00 .000 .2498E-02 .5142E-02 .1177E-01
12.00 .000 .2863E-02 .5872E-02 .1334E-01
14.00 .000 .3228E-02 .6602E-02 .1492E-01
15.00 .000 .3411E-02 .6968E-02 .1570E-01
16.00 .000 .3594E-02 .7333E-02 .1649E-01
17.00 .000 .3776E-02 .7698E-02 .1727E-01
18.00 .000 .3959E-02 .8063E-02 .1806E-01
20.00 .000 .4324E-02 .8794E-02 .1963E-01
22.00 .000 .4689E-02 .9524E-02 .2120E-01
24.00 .000 .5054E-02 .1025E-01 .2277E-01
Drag Coefficient due to Elevator Deflection
Positive surface deflection is trailing edge down
aero/qbar-psf
metrics/Sw-sqft
aero/alpha-rad
fcs/elevator-pos-rad
-.3491 -.2618 -.1745 -.8727E-01 .000 .8727E-01 .1745 .2618 .3491
-.2793 .1322E-01 .1247E-01 .7884E-02 .3304E-02 -.5331E-05 -.2029E-02 -.2784E-02 -.2468E-02 -.2352E-02
-.1745 .1010E-01 .9482E-02 .5748E-02 .2237E-02 -.3196E-05 -.9616E-03 -.6481E-03 .5232E-03 .7662E-03
-.1396 .9101E-02 .8520E-02 .5061E-02 .1893E-02 -.2508E-05 -.6180E-03 .3911E-04 .1486E-02 .1770E-02
-.1047 .8094E-02 .7554E-02 .4371E-02 .1548E-02 -.1819E-05 -.2732E-03 .7287E-03 .2452E-02 .2776E-02
-.6981E-01 .7113E-02 .6613E-02 .3699E-02 .1212E-02 -.1147E-05 .6281E-04 .1401E-02 .3393E-02 .3757E-02
-.3491E-01 .6175E-02 .5712E-02 .3056E-02 .8907E-03 -.5039E-06 .3843E-03 .2044E-02 .4293E-02 .4696E-02
.000 .5277E-02 .4851E-02 .2442E-02 .5833E-03 .1110E-06 .6917E-03 .2658E-02 .5155E-02 .5594E-02
.3491E-01 .4408E-02 .4017E-02 .1846E-02 .2855E-03 .7066E-06 .9895E-03 .3254E-02 .5989E-02 .6463E-02
.6981E-01 .3474E-02 .3121E-02 .1206E-02 -.3437E-04 .1346E-05 .1309E-02 .3894E-02 .6885E-02 .7397E-02
.1396 .1391E-02 .1122E-02 -.2204E-03 -.7477E-03 .2773E-05 .2023E-02 .5320E-02 .8883E-02 .9480E-02
.1745 .1802E-03 -.3896E-04 -.1049E-02 -.1162E-02 .3602E-05 .2437E-02 .6150E-02 .1004E-01 .1069E-01
.2094 -.1233E-02 -.1395E-02 -.2018E-02 -.1646E-02 .4570E-05 .2921E-02 .7118E-02 .1140E-01 .1210E-01
.2443 -.2847E-02 -.2943E-02 -.3123E-02 -.2199E-02 .5675E-05 .3474E-02 .8223E-02 .1295E-01 .1372E-01
.2618 -.3708E-02 -.3769E-02 -.3713E-02 -.2494E-02 .6265E-05 .3769E-02 .8813E-02 .1377E-01 .1458E-01
.2793 -.5045E-02 -.5052E-02 -.4629E-02 -.2952E-02 .7182E-05 .4227E-02 .9729E-02 .1506E-01 .1592E-01
.2967 -.6388E-02 -.6341E-02 -.5549E-02 -.3412E-02 .8102E-05 .4687E-02 .1065E-01 .1635E-01 .1726E-01
.3142 -.8765E-02 -.8621E-02 -.7177E-02 -.4226E-02 .9724E-05 .5501E-02 .1228E-01 .1863E-01 .1964E-01
.3491 -.1217E-01 -.1188E-01 -.9506E-02 -.5391E-02 .1206E-04 .6666E-02 .1461E-01 .2189E-01 .2304E-01
.3840 -.1534E-01 -.1493E-01 -.1168E-01 -.6477E-02 .1424E-04 .7752E-02 .1678E-01 .2493E-01 .2621E-01
.4189 -.1816E-01 -.1764E-01 -.1361E-01 -.7444E-02 .1615E-04 .8719E-02 .1871E-01 .2764E-01 .2903E-01
Side Force coefficient due to Sideslip
Contributes to damping of Dutch Roll mode
aero/qbar-psf
metrics/Sw-sqft
aero/beta-rad
aero/alpha-rad
-.2793 -.5277
-.1745 -.5277
-.1396 -.5277
-.1047 -.5277
-.6981E-01 -.5277
-.3491E-01 -.5277
.000 -.5277
.3491E-01 -.5277
.6981E-01 -.5277
.1396 -.5277
.1745 -.5277
.2094 -.5277
.2443 -.5277
.2618 -.5277
.2793 -.5277
.2967 -.5277
.3142 -.5277
.3491 -.5277
.3840 -.5277
.4189 -.5277
Side Force Coefficient due to Roll Rate
velocities/p-aero-rad_sec
aero/qbar-psf
metrics/Sw-sqft
aero/bi2vel
aero/alpha-rad
-.2793 -.8364E-01
-.1745 -.1082
-.1396 -.1154
-.1047 -.1221
-.6981E-01 -.1295
-.3491E-01 -.1385
.000 -.1496
.3491E-01 -.1635
.6981E-01 -.1827
.1396 .1989
.1745 -.1426
.2094 -.1626
.2443 -.1731
.2618 -.1675
.2793 -.1696
.2967 -.1282
.3142 -.7662E-01
.3491 .3365E-02
.3840 .7152E-01
.4189 .1194
Side Force due to Yaw Rate (DATCOM does not calculate)
Effect is small
aero/qbar-psf
metrics/Sw-sqft
aero/bi2vel
velocities/r-aero-rad_sec
.000
Side Force due to rudder (DATCOM does not calculate)
aero/qbar-psf
metrics/Sw-sqft
fcs/rudder-pos-rad
.000
Side Force due to aileron (DATCOM does not calculate)
Usually neglected
aero/qbar-psf
metrics/Sw-sqft
metrics/Sw-sqft
fcs/left-aileron-pos-rad
.000
Roll Moment coefficient due to Beta
Decrease of Clb 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
aero/beta-rad
aero/alpha-rad
-.2793 -.1357
-.1745 -.1271
-.1396 -.1240
-.1047 -.1208
-.6981E-01 -.1175
-.3491E-01 -.1142
.000 -.1110
.3491E-01 -.1079
.6981E-01 -.1048
.1396 -.9820E-01
.1745 -.9428E-01
.2094 -.8986E-01
.2443 -.8483E-01
.2618 -.8170E-01
.2793 -.7824E-01
.2967 -.7208E-01
.3142 -.6456E-01
.3491 -.5134E-01
.3840 -.3930E-01
.4189 -.2910E-01
Roll Moment coefficient due to roll rate
Clp alone determines damping-in-roll characteristics
aero/qbar-psf
metrics/Sw-sqft
metrics/bw-ft
aero/bi2vel
velocities/p-aero-rad_sec
-1.0
aero/alpha-deg
-16.00 .3294
-10.00 .3162
-8.000 .3085
-6.000 .3066
-4.000 .3176
-2.000 .3313
.000 .3415
2.000 .3479
4.000 .3366
8.000 .2403
10.00 .1712
12.00 .9202E-01
14.00 -.8719E-01
15.00 -.1715
16.00 -.6740
17.00 -1.212
18.00 -1.159
20.00 -.8836
22.00 -.6817
24.00 -.4080
Roll Moment coefficient due to yaw rate
Considerable effect on Spiral mode. Large
positive values leads to strong sprial instability
aero/qbar-psf
metrics/Sw-sqft
metrics/bw-ft
aero/bi2vel
velocities/r-aero-rad_sec
aero/alpha-deg
-16.00 -.1690
-10.00 -.4933E-01
-8.000 -.1181E-01
-6.000 .2396E-01
-4.000 .6027E-01
-2.000 .9837E-01
.000 .1379
2.000 .1786
4.000 .2199
8.000 .2927
10.00 .3160
12.00 .3307
14.00 .3341
15.00 .3227
16.00 .3091
17.00 .2319
18.00 .1476
20.00 .2074E-01
22.00 -.8871E-01
24.00 -.1616
Roll Moment coefficient due to Left Double Slotted Flaps Deflection
aero/qbar-psf
metrics/Sw-sqft
metrics/bw-ft
fcs/left-aileron-pos-rad
-.6981 -.7359E-01
-.3491 -.4245E-01
-.1745 -.2123E-01
-.8727E-01 -.1061E-01
.000 .000
.8727E-01 .1061E-01
.1745 .2123E-01
.3491 .4245E-01
.6981 .7359E-01
Roll Moment Coefficient due to Asymetrical Fowler Flaps Deflection
calculated as difference between left and right flap lift coef,
times distance from centerline to MAC of surface.
12.24
aero/coefficient/CLdF3R
aero/coefficient/CLdF3L
Roll moment due to rudder (DATCOM does not calculate)
Usually insignificant in dynamic stability considerations
but is used in autopilot work
metrics/bw-ft
aero/qbar-psf
metrics/Sw-sqft
fcs/rudder-pos-rad
.000
Basic_Pitch_moment_coefficient
aero/qbar-psf
metrics/Sw-sqft
metrics/cbarw-ft
aero/alpha-rad
-.2793 .3419
-.1745 .2024
-.1396 .1567
-.1047 .1096
-.6981E-01 .6524E-01
-.3491E-01 .2272E-01
.000 -.1663E-01
.3491E-01 -.5525E-01
.6981E-01 -.9550E-01
.1396 -.1824
.1745 -.2293
.2094 -.2787
.2443 -.2787
.2618 -.2787
.2793 -.2787
.2967 -.2787
.3142 -.2787
.3491 -.2787
.3840 -.2787
.4189 -.2787
Pitch moment coefficient due to pitch rate(per radian)
Pitch Damping Derivative
Very important to Short Period damping of oscillations
aero/qbar-psf
metrics/Sw-sqft
metrics/cbarw-ft
aero/ci2vel
velocities/q-aero-rad_sec
aero/alpha-rad
-.2793 -11.21
-.1745 -11.21
-.1396 -11.21
-.1047 -11.21
-.6981E-01 -11.21
-.3491E-01 -11.21
.000 -11.21
.3491E-01 -11.21
.6981E-01 -11.21
.1396 -11.21
.1745 -11.21
.2094 -11.21
.2443 -11.21
.2618 -11.21
.2793 -11.21
.2967 -11.21
.3142 -11.21
.3491 -11.21
.3840 -11.21
.4189 -11.21
Pitch moment coefficient due to AOA rate(per radian)
Negitive Cmad increase Short Period damping
aero/qbar-psf
metrics/Sw-sqft
metrics/cbarw-ft
aero/ci2vel
aero/alphadot-rad_sec
aero/alpha-rad
-.2793 -5.541
-.1745 -5.721
-.1396 -5.770
-.1047 -5.845
-.6981E-01 -6.073
-.3491E-01 -6.351
.000 -6.583
.3491E-01 -6.461
.6981E-01 -6.006
.1396 -4.772
.1745 -3.715
.2094 -2.300
.2443 -1.111
.2618 2.161
.2793 5.443
.2967 12.40
.3142 16.30
.3491 9.499
.3840 7.571
.4189 6.410
Pitch moment coefficient due to elevator deflection
Positive surface deflection is trailing edge down
aero/qbar-psf
metrics/Sw-sqft
metrics/cbarw-ft
fcs/elevator-pos-rad
-.3491 .2876
-.2618 .2748
-.1745 .1961
-.8727E-01 .9804E-01
.000 -.1961E-03
.8727E-01 -.9804E-01
.1745 -.1961
.2618 -.2748
.3491 -.2880
Pitch moment coefficient due to left Fowler Flaps Deflection
Positive surface deflection is trailing edge down
Ultimately, we will feed this left flap pos
aero/qbar-psf
metrics/Sw-sqft
metrics/cbarw-ft
fcs/flap-pos-deg
.000 .000
8.000 -.1259E-02
12.00 -.2519E-02
25.00 -.5416E-02
Pitch moment coefficient due to right Fowler Flaps Deflection
Positive surface deflection is trailing edge down
Ultimately, we will feed this right flap pos
aero/qbar-psf
metrics/Sw-sqft
metrics/cbarw-ft
fcs/flap-pos-deg
.000 .000
8.000 -.1259E-02
12.00 -.2519E-02
25.00 -.5416E-02
Yaw moment coefficient due to sideslip(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
-.2793 .7888E-01
-.1745 .7888E-01
-.1396 .7888E-01
-.1047 .7888E-01
-.6981E-01 .7888E-01
-.3491E-01 .7888E-01
.000 .7888E-01
.3491E-01 .7888E-01
.6981E-01 .7888E-01
.1396 .7888E-01
.1745 .7888E-01
.2094 .7888E-01
.2443 .7888E-01
.2618 .7888E-01
.2793 .7888E-01
.2967 .7888E-01
.3142 .7888E-01
.3491 .7888E-01
.3840 .7888E-01
.4189 .7888E-01
Yaw moment coefficient due to roll rate(per radian)
Reduces Dutch Roll damping
positive value desireable
aero/qbar-psf
metrics/Sw-sqft
metrics/bw-ft
aero/bi2vel
velocities/p-aero-rad_sec
aero/alpha-rad
-.2793 .1331
-.1745 .6090E-01
-.1396 .3657E-01
-.1047 .1245E-01
-.6981E-01 -.1281E-01
-.3491E-01 -.4026E-01
.000 -.7038E-01
.3491E-01 -.1042
.6981E-01 -.1439
.1396 .3362
.1745 -.1310
.2094 -.1723
.2443 -.1992
.2618 -.2013
.2793 -.2039
.2967 -.1671
.3142 -.1321
.3491 -.8233E-01
.3840 -.3845E-01
.4189 -.1051E-01
Yaw Moment coefficient due to yaw rate(per radian)
Main contributor to damping of Dutch Roll
aero/qbar-psf
metrics/Sw-sqft
metrics/bw-ft
aero/bi2vel
velocities/r-aero-rad_sec
aero/alpha-rad
-.2793 -.1414
-.1745 -.1455
-.1396 -.1472
-.1047 -.1490
-.6981E-01 -.1509
-.3491E-01 -.1528
.000 -.1549
.3491E-01 -.1571
.6981E-01 -.1595
.1396 -.1641
.1745 -.1653
.2094 -.1656
.2443 -.1647
.2618 -.1630
.2793 -.1610
.2967 -.1543
.3142 -.1486
.3491 -.1422
.3840 -.1388
.4189 -.1367
Yaw Moment Coefficient due to Asymetrical Fowler Flaps Deflection
calculated as difference between left and right flap drag coef,
times distance from centerline to MAC of surface.
12.24
aero/coefficient/CdDf3R
aero/coefficient/CdDf3L
Yaw Moment coefficient due to plain flap aileron deflection
aero/qbar-psf
metrics/Sw-sqft
metrics/bw-ft
aero/alpha-rad
fcs/left-aileron-pos-rad
-.6981 -.3491 -.1745 -.8727E-01 .000 .8727E-01 .1745 .3491 .6981
-.2793 -.9212E-02 -.5320E-02 -.2660E-02 -.1330E-02 .000 .1330E-02 .2660E-02 .5320E-02 .9212E-02
-.1745 -.3389E-02 -.1957E-02 -.9785E-03 -.4893E-03 .000 .4893E-03 .9785E-03 .1957E-02 .3389E-02
-.1396 -.1536E-02 -.8868E-03 -.4434E-03 -.2217E-03 .000 .2217E-03 .4434E-03 .8868E-03 .1536E-02
-.1047 .2470E-03 .1427E-03 .7133E-04 .3566E-04 .000 -.3566E-04 -.7133E-04 -.1427E-03 -.2470E-03
-.6981E-01 .2059E-02 .1189E-02 .5945E-03 .2973E-03 .000 -.2973E-03 -.5945E-03 -.1189E-02 -.2059E-02
-.3491E-01 .3954E-02 .2283E-02 .1142E-02 .5709E-03 .000 -.5709E-03 -.1142E-02 -.2283E-02 -.3954E-02
.000 .5916E-02 .3416E-02 .1708E-02 .8541E-03 .000 -.8541E-03 -.1708E-02 -.3416E-02 -.5916E-02
.3491E-01 .7928E-02 .4578E-02 .2289E-02 .1145E-02 .000 -.1145E-02 -.2289E-02 -.4578E-02 -.7928E-02
.6981E-01 .9972E-02 .5759E-02 .2879E-02 .1440E-02 .000 -.1440E-02 -.2879E-02 -.5759E-02 -.9972E-02
.1396 .1362E-01 .7866E-02 .3933E-02 .1967E-02 .000 -.1967E-02 -.3933E-02 -.7866E-02 -.1362E-01
.1745 .1487E-01 .8588E-02 .4294E-02 .2147E-02 .000 -.2147E-02 -.4294E-02 -.8588E-02 -.1487E-01
.2094 .1574E-01 .9088E-02 .4544E-02 .2272E-02 .000 -.2272E-02 -.4544E-02 -.9088E-02 -.1574E-01
.2443 .1611E-01 .9301E-02 .4651E-02 .2325E-02 .000 -.2325E-02 -.4651E-02 -.9301E-02 -.1611E-01
.2618 .1571E-01 .9074E-02 .4537E-02 .2269E-02 .000 -.2269E-02 -.4537E-02 -.9074E-02 -.1571E-01
.2793 .1522E-01 .8791E-02 .4396E-02 .2198E-02 .000 -.2198E-02 -.4396E-02 -.8791E-02 -.1522E-01
.2967 .1194E-01 .6897E-02 .3449E-02 .1724E-02 .000 -.1724E-02 -.3449E-02 -.6897E-02 -.1194E-01
.3142 .8353E-02 .4824E-02 .2412E-02 .1206E-02 .000 -.1206E-02 -.2412E-02 -.4824E-02 -.8353E-02
.3491 .2989E-02 .1726E-02 .8630E-03 .4315E-03 .000 -.4315E-03 -.8630E-03 -.1726E-02 -.2989E-02
.3840 -.1619E-02 -.9348E-03 -.4674E-03 -.2337E-03 .000 .2337E-03 .4674E-03 .9348E-03 .1619E-02
.4189 -.4633E-02 -.2676E-02 -.1338E-02 -.6689E-03 .000 .6689E-03 .1338E-02 .2676E-02 .4633E-02
Yaw Coefficient due to rudder (DATCOM does not calculate)
High value for controllablity, low value
for good dynamic stability
aero/qbar-psf
metrics/Sw-sqft
metrics/bw-ft
fcs/rudder-pos-rad
-.6000E-01
Elevator hinge moment in ft-lbs
HM = q * S * Cbar * ( Ch0 + Cha*alpha + Chd*delta )
Positive causes trailing edge down movement
Ch0 is used to artifically trim HM to zero
aero/qbar-psf
metrics/Sw-sqft
41.86
3.113
aero/alpha-rad
aero/alpha-rad
-.2793 -.7460E-02
-.1745 -.7460E-02
-.1396 -.7460E-02
-.1047 -.7460E-02
-.6981E-01 -.7460E-02
-.3491E-01 -.7460E-02
.000 -.7460E-02
.3491E-01 -.7460E-02
.6981E-01 -.7460E-02
.1396 -.7460E-02
.1745 -.1254E-01
.2094 -.1145E-01
.2443 -.1110E-01
.2618 -.1110E-01
.2793 -.1110E-01
.2967 -.1110E-01
.3142 -.1110E-01
.3491 -.1145E-01
.3840 -.1254E-01
.4189 -.1110E-01
fcs/elevator-pos-rad
fcs/elevator-pos-rad
-.3491 -.1254E-01
-.2618 -.1145E-01
-.1745 -.1110E-01
-.8727E-01 -.1110E-01
.000 -.1110E-01
.8727E-01 -.1110E-01
.1745 -.1110E-01
.2618 -.1145E-01
.3491 -.1254E-01