public static void AddExtra(Aerodata aero)
{
var mach_table = @"0.202 1.2579450
0.306 1.1412150
0.400 1.0627178
0.503 1.0219124
0.608 1.0000000
0.705 0.9909509
0.802 1.0008701
0.901 1.0107093
0.923 1.0417084
0.934 1.0793344
0.945 1.1295980
1.009 1.8800483
1.029 2.0249037
1.048 2.1444697
1.092 2.2317526
1.170 2.2611620
1.603 2.1857642
1.797 2.1360697
1.948 2.0812627
1.999 2.0608600
2.091 2.0330027
";
var ad = aero.Add("Lift Mach factor (NASA-TM-84643 Figure 3 Clalpha) and values for AOA derived from NASA-aaia-2000-0900 Figure 4", "ClMach", "mach");
ad.data = parse(ad, 1, mach_table);
ad = aero.Add("Yaw factor (NASA-TM-84643 Figure 3 Clalpha) and values for AOA derived from NASA-aaia-2000-0900 Figure 4", "CyMach", "mach");
ad.data = parse(ad, 1, mach_table);
ad = aero.Add("Roll Mach factor (NASA-TM-84643 Figure 3 Clalpha) and values for AOA derived from NASA-aaia-2000-0900 Figure 4", "CLMach", "mach");
ad.data = parse(ad, 1, mach_table);
ad = aero.Add("Pitch Mach factor (NASA-TM-84643 Figure 3 Clalpha) and values for AOA derived from NASA-aaia-2000-0900 Figure 4", "CMMach", "mach");
ad.data = parse(ad, 1, mach_table);
ad = aero.Add("Yaw Mach factor (NASA-TM-84643 Figure 3 Clalpha) and values for AOA derived from NASA-aaia-2000-0900 Figure 4", "CNMach", "mach");
ad.data = parse(ad, 1, mach_table);
// var ad = aero.Add("Lift Mach factor (NASA-TM-84643 Figure 3 Clalpha) and values for AOA derived from NASA-aaia-2000-0900 Figure 4", "ClMach", "mach", "alpha");
// ad.data = parse(ad, 2, @" 0.0 0.2 0.6 0.9 1.1 1.3 1.5 1.8 2.1 2.6 3.0
// -20 1.00000000 1.00000000 0.96610485 1.23950808 1.41632259 1.34327421 1.13294356 0.93062904 0.76851372 0.58968226 0.51614275
// -15 1.00000000 1.00000000 0.96116198 1.23316641 1.40907629 1.33640164 1.12714710 0.92586768 0.76458179 0.58666528 0.51350202
// -10 1.00000000 1.00000000 0.99142346 1.27199174 1.45344001 1.37847726 1.16263449 0.95501794 0.78865408 0.60513601 0.52966925
// -5 1.00000000 1.00000000 0.96759116 1.24141501 1.41850155 1.34534078 1.13468655 0.93206078 0.76969605 0.59058947 0.51693681
// 4 1.00000000 1.00000000 0.95837601 1.22959201 1.40499202 1.33252801 1.12388001 0.92318401 0.76236561 0.58496481 0.51201361
// 8 1.00000000 1.00000000 0.99142346 1.27199174 1.45344001 1.37847726 1.16263449 0.95501794 0.78865408 0.60513601 0.52966925
// 12 1.00000000 1.00000000 0.96759116 1.24141501 1.41850155 1.34534078 1.13468655 0.93206078 0.76969605 0.59058947 0.51693681
// 16 1.00000000 1.00000000 0.98015728 1.25753729 1.43692365 1.36281274 1.14942274 0.94416546 0.77969210 0.59825946 0.52365028
// 20 1.00000000 1.00000000 0.96074823 1.23263556 1.40846972 1.33582635 1.12666189 0.92546912 0.76425265 0.58641274 0.51328097
// 24 1.00000000 1.00000000 0.96503140 1.23813085 1.41474891 1.34178168 1.13168474 0.92959501 0.76765981 0.58902706 0.51556926
// 28 1.00000000 1.00000000 0.96044147 1.23224199 1.40802001 1.33539984 1.12630217 0.92517363 0.76400864 0.58622551 0.51311708
// 32 1.00000000 1.00000000 0.96642959 1.23992472 1.41679867 1.34372573 1.13332438 0.93094186 0.76877204 0.58988048 0.51631624
// 40 1.00000000 1.00000000 0.95223257 1.22171001 1.39598566 1.32398617 1.11667565 0.91726616 0.75747865 0.58121503 0.50873147
// 45 1.00000000 1.00000000 0.95617790 1.22677185 1.40176956 1.32947176 1.12130231 0.92106662 0.76061706 0.58362314 0.51083926
// 50 1.00000000 1.00000000 0.95837601 1.22959201 1.40499202 1.33252801 1.12388001 0.92318401 0.76236561 0.58496481 0.51201361
//");
// ad = aero.Add("Sideforce Mach factor (NASA-TM-84643 Figure 3 Clalpha) and values for AOA derived from NASA-aaia-2000-0900 Figure 4", "CyMach", "mach", "alpha");
// ad.data = parse(ad, 2, @" 0.0 0.2 0.6 0.9 1.1 1.3 1.5 1.8 2.1 2.6 3.0
// -20 1.00000000 1.00000000 0.96610485 1.23950808 1.41632259 1.34327421 1.13294356 0.93062904 0.76851372 0.58968226 0.51614275
// -15 1.00000000 1.00000000 0.96116198 1.23316641 1.40907629 1.33640164 1.12714710 0.92586768 0.76458179 0.58666528 0.51350202
// -10 1.00000000 1.00000000 0.99142346 1.27199174 1.45344001 1.37847726 1.16263449 0.95501794 0.78865408 0.60513601 0.52966925
// -5 1.00000000 1.00000000 0.96759116 1.24141501 1.41850155 1.34534078 1.13468655 0.93206078 0.76969605 0.59058947 0.51693681
// 4 1.00000000 1.00000000 0.95837601 1.22959201 1.40499202 1.33252801 1.12388001 0.92318401 0.76236561 0.58496481 0.51201361
// 8 1.00000000 1.00000000 0.99142346 1.27199174 1.45344001 1.37847726 1.16263449 0.95501794 0.78865408 0.60513601 0.52966925
// 12 1.00000000 1.00000000 0.96759116 1.24141501 1.41850155 1.34534078 1.13468655 0.93206078 0.76969605 0.59058947 0.51693681
// 16 1.00000000 1.00000000 0.98015728 1.25753729 1.43692365 1.36281274 1.14942274 0.94416546 0.77969210 0.59825946 0.52365028
// 20 1.00000000 1.00000000 0.96074823 1.23263556 1.40846972 1.33582635 1.12666189 0.92546912 0.76425265 0.58641274 0.51328097
// 24 1.00000000 1.00000000 0.96503140 1.23813085 1.41474891 1.34178168 1.13168474 0.92959501 0.76765981 0.58902706 0.51556926
// 28 1.00000000 1.00000000 0.96044147 1.23224199 1.40802001 1.33539984 1.12630217 0.92517363 0.76400864 0.58622551 0.51311708
// 32 1.00000000 1.00000000 0.96642959 1.23992472 1.41679867 1.34372573 1.13332438 0.93094186 0.76877204 0.58988048 0.51631624
// 40 1.00000000 1.00000000 0.95223257 1.22171001 1.39598566 1.32398617 1.11667565 0.91726616 0.75747865 0.58121503 0.50873147
// 45 1.00000000 1.00000000 0.95617790 1.22677185 1.40176956 1.32947176 1.12130231 0.92106662 0.76061706 0.58362314 0.51083926
// 50 1.00000000 1.00000000 0.95837601 1.22959201 1.40499202 1.33252801 1.12388001 0.92318401 0.76236561 0.58496481 0.51201361
//");
// ad = aero.Add("Roll Mach factor (NASA-TM-84643 Figure 3 Clalpha) and values for AOA derived from NASA-aaia-2000-0900 Figure 4", "CLMach", "mach", "alpha");
// ad.data = parse(ad, 2, @" 0.0 0.2 0.6 0.9 1.1 1.3 1.5 1.8 2.1 2.6 3.0
// -20 1.00000000 1.00000000 0.96610485 1.23950808 1.41632259 1.34327421 1.13294356 0.93062904 0.76851372 0.58968226 0.51614275
// -15 1.00000000 1.00000000 0.96116198 1.23316641 1.40907629 1.33640164 1.12714710 0.92586768 0.76458179 0.58666528 0.51350202
// -10 1.00000000 1.00000000 0.99142346 1.27199174 1.45344001 1.37847726 1.16263449 0.95501794 0.78865408 0.60513601 0.52966925
// -5 1.00000000 1.00000000 0.96759116 1.24141501 1.41850155 1.34534078 1.13468655 0.93206078 0.76969605 0.59058947 0.51693681
// 4 1.00000000 1.00000000 0.95837601 1.22959201 1.40499202 1.33252801 1.12388001 0.92318401 0.76236561 0.58496481 0.51201361
// 8 1.00000000 1.00000000 0.99142346 1.27199174 1.45344001 1.37847726 1.16263449 0.95501794 0.78865408 0.60513601 0.52966925
// 12 1.00000000 1.00000000 0.96759116 1.24141501 1.41850155 1.34534078 1.13468655 0.93206078 0.76969605 0.59058947 0.51693681
// 16 1.00000000 1.00000000 0.98015728 1.25753729 1.43692365 1.36281274 1.14942274 0.94416546 0.77969210 0.59825946 0.52365028
// 20 1.00000000 1.00000000 0.96074823 1.23263556 1.40846972 1.33582635 1.12666189 0.92546912 0.76425265 0.58641274 0.51328097
// 24 1.00000000 1.00000000 0.96503140 1.23813085 1.41474891 1.34178168 1.13168474 0.92959501 0.76765981 0.58902706 0.51556926
// 28 1.00000000 1.00000000 0.96044147 1.23224199 1.40802001 1.33539984 1.12630217 0.92517363 0.76400864 0.58622551 0.51311708
// 32 1.00000000 1.00000000 0.96642959 1.23992472 1.41679867 1.34372573 1.13332438 0.93094186 0.76877204 0.58988048 0.51631624
// 40 1.00000000 1.00000000 0.95223257 1.22171001 1.39598566 1.32398617 1.11667565 0.91726616 0.75747865 0.58121503 0.50873147
// 45 1.00000000 1.00000000 0.95617790 1.22677185 1.40176956 1.32947176 1.12130231 0.92106662 0.76061706 0.58362314 0.51083926
// 50 1.00000000 1.00000000 0.95837601 1.22959201 1.40499202 1.33252801 1.12388001 0.92318401 0.76236561 0.58496481 0.51201361
//");
// ad = aero.Add("Pitch Mach factor (NASA-TM-84643 Figure 3 Clalpha) and values for AOA derived from NASA-aaia-2000-0900 Figure 4", "CMMach", "mach", "alpha");
// ad.data = parse(ad, 2, @" 0.0 0.2 0.6 0.9 1.1 1.3 1.5 1.8 2.1 2.6 3.0
// -20 1.00000000 1.00000000 0.96610485 1.23950808 1.41632259 1.34327421 1.13294356 0.93062904 0.76851372 0.58968226 0.51614275
// -15 1.00000000 1.00000000 0.96116198 1.23316641 1.40907629 1.33640164 1.12714710 0.92586768 0.76458179 0.58666528 0.51350202
// -10 1.00000000 1.00000000 0.99142346 1.27199174 1.45344001 1.37847726 1.16263449 0.95501794 0.78865408 0.60513601 0.52966925
// -5 1.00000000 1.00000000 0.96759116 1.24141501 1.41850155 1.34534078 1.13468655 0.93206078 0.76969605 0.59058947 0.51693681
// 4 1.00000000 1.00000000 0.95837601 1.22959201 1.40499202 1.33252801 1.12388001 0.92318401 0.76236561 0.58496481 0.51201361
// 8 1.00000000 1.00000000 0.99142346 1.27199174 1.45344001 1.37847726 1.16263449 0.95501794 0.78865408 0.60513601 0.52966925
// 12 1.00000000 1.00000000 0.96759116 1.24141501 1.41850155 1.34534078 1.13468655 0.93206078 0.76969605 0.59058947 0.51693681
// 16 1.00000000 1.00000000 0.98015728 1.25753729 1.43692365 1.36281274 1.14942274 0.94416546 0.77969210 0.59825946 0.52365028
// 20 1.00000000 1.00000000 0.96074823 1.23263556 1.40846972 1.33582635 1.12666189 0.92546912 0.76425265 0.58641274 0.51328097
// 24 1.00000000 1.00000000 0.96503140 1.23813085 1.41474891 1.34178168 1.13168474 0.92959501 0.76765981 0.58902706 0.51556926
// 28 1.00000000 1.00000000 0.96044147 1.23224199 1.40802001 1.33539984 1.12630217 0.92517363 0.76400864 0.58622551 0.51311708
// 32 1.00000000 1.00000000 0.96642959 1.23992472 1.41679867 1.34372573 1.13332438 0.93094186 0.76877204 0.58988048 0.51631624
// 40 1.00000000 1.00000000 0.95223257 1.22171001 1.39598566 1.32398617 1.11667565 0.91726616 0.75747865 0.58121503 0.50873147
// 45 1.00000000 1.00000000 0.95617790 1.22677185 1.40176956 1.32947176 1.12130231 0.92106662 0.76061706 0.58362314 0.51083926
// 50 1.00000000 1.00000000 0.95837601 1.22959201 1.40499202 1.33252801 1.12388001 0.92318401 0.76236561 0.58496481 0.51201361
//");
// ad = aero.Add("Yaw Mach factor (NASA-TM-84643 Figure 3 Clalpha) and values for AOA derived from NASA-aaia-2000-0900 Figure 4", "CNMach", "mach", "alpha");
// ad.data = parse(ad, 2, @" 0.0 0.2 0.6 0.9 1.1 1.3 1.5 1.8 2.1 2.6 3.0
// -20 1.00000000 1.00000000 0.96610485 1.23950808 1.41632259 1.34327421 1.13294356 0.93062904 0.76851372 0.58968226 0.51614275
// -15 1.00000000 1.00000000 0.96116198 1.23316641 1.40907629 1.33640164 1.12714710 0.92586768 0.76458179 0.58666528 0.51350202
// -10 1.00000000 1.00000000 0.99142346 1.27199174 1.45344001 1.37847726 1.16263449 0.95501794 0.78865408 0.60513601 0.52966925
// -5 1.00000000 1.00000000 0.96759116 1.24141501 1.41850155 1.34534078 1.13468655 0.93206078 0.76969605 0.59058947 0.51693681
// 4 1.00000000 1.00000000 0.95837601 1.22959201 1.40499202 1.33252801 1.12388001 0.92318401 0.76236561 0.58496481 0.51201361
// 8 1.00000000 1.00000000 0.99142346 1.27199174 1.45344001 1.37847726 1.16263449 0.95501794 0.78865408 0.60513601 0.52966925
// 12 1.00000000 1.00000000 0.96759116 1.24141501 1.41850155 1.34534078 1.13468655 0.93206078 0.76969605 0.59058947 0.51693681
// 16 1.00000000 1.00000000 0.98015728 1.25753729 1.43692365 1.36281274 1.14942274 0.94416546 0.77969210 0.59825946 0.52365028
// 20 1.00000000 1.00000000 0.96074823 1.23263556 1.40846972 1.33582635 1.12666189 0.92546912 0.76425265 0.58641274 0.51328097
// 24 1.00000000 1.00000000 0.96503140 1.23813085 1.41474891 1.34178168 1.13168474 0.92959501 0.76765981 0.58902706 0.51556926
// 28 1.00000000 1.00000000 0.96044147 1.23224199 1.40802001 1.33539984 1.12630217 0.92517363 0.76400864 0.58622551 0.51311708
// 32 1.00000000 1.00000000 0.96642959 1.23992472 1.41679867 1.34372573 1.13332438 0.93094186 0.76877204 0.58988048 0.51631624
// 40 1.00000000 1.00000000 0.95223257 1.22171001 1.39598566 1.32398617 1.11667565 0.91726616 0.75747865 0.58121503 0.50873147
// 45 1.00000000 1.00000000 0.95617790 1.22677185 1.40176956 1.32947176 1.12130231 0.92106662 0.76061706 0.58362314 0.51083926
// 50 1.00000000 1.00000000 0.95837601 1.22959201 1.40499202 1.33252801 1.12388001 0.92318401 0.76236561 0.58496481 0.51201361
//");
ad = aero.Add("Incremental Cd due to external tanks", "CdTNK", "mach");
ad.AddFactor("fcs/external-tanks-fitted");
ad.data = parse(ad, 1, @"0.4 0.0005
0.6 0.0005
0.7 0.0005
0.8 0.0005
0.85 0.0011
0.9 0.0065
0.94 0.0074
0.98 0.0077
1 0.0078
1.1 0.0079
1.2 0.0080
2 0.0081");
ad = aero.Add("Delta Cl due to mean flap position", "ClDFM", "alpha", "fcs/flap-pos-deg");
ad.data = parse(ad, 2, @" -20 -5 0 5 10 25 50
0 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000
10 -0.01400 -0.13160 0.13440 0.13160 0.12880 0.10920 0.01400
35 -0.09016 -0.25872 0.25480 0.25872 0.29872 0.21560 0.22540
50 -0.24500 -0.60200 0.59500 0.60200 0.58800 0.46200 0.24500
");
ad = aero.Add("Cl increment due to gear", "ClUC", "alpha");
ad.AddFactor("gear/gear-pos-norm");
ad.data = parse(ad, 1, @"-10 -0.00
0 -0.0012
8 -0.0010
12 -0.0004
14 -0.0002
16 -0.0001
18 -0.000");
ad = aero.Add("Cd increment due to gear", "CdUC", "alpha");
ad.AddFactor("gear/gear-pos-norm");
ad.data = parse(ad, 1, @" -10 0
-5 0.00017
0 0.00001
5 0.00005
10 0");
ad = aero.Add("Drag due to speedbrakes", "CdDBRK", "alpha");
ad.AddFactor("fcs/speedbrake-pos-norm");
ad.data = parse(ad, 1, @" -25 0.0210
-20 0.0310
-15 0.0414
-5 0.0650
0 0.0784
5 0.0650
15 0.0514
35 0.0210
40 0.0188");
ad = aero.Add("Drag mach factor (NASA CR-152391-VOL-1 Figure 3-2 p54)", "CdMach", "mach");
ad.data = parse(ad, 1, @"
0.202 1.2579450
0.306 1.1412150
0.400 1.0627178
0.503 1.0219124
0.608 1.0000000
0.705 0.9909509
0.802 1.0008701
0.901 1.0107093
0.923 1.0417084
0.934 1.0793344
0.945 1.1295980
1.009 1.8800483
1.029 2.0249037
1.048 2.1444697
1.092 2.2317526
1.170 2.2611620
1.603 2.1857642
1.797 2.1360697
1.948 2.0812627
1.999 2.0608600
2.091 2.0330027
");
ad = aero.Add("Delta Cd due to mean flap position", "CdDFM", "alpha", "fcs/flap-pos-deg");
ad.data = parse(ad, 2, @" -20 -5 0 5 10 25 50
0 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000
10 0.01400 0.02268 0.01932 0.02268 0.02548 0.02856 0.09590
35 0.09016 0.06894 0.06222 0.06894 0.09862 0.14286 0.55734");
ad = aero.Add("Pitch moment increment due to aim missiles", "DCMAIM", "alpha", "mach");
ad.AddFactor("fcs/aim-fitted");
ad.data = parse(ad, 2, @"-6 -5 -4 -3 -2 -1 0 1 2 3 4 5 6 7 8 9 10 20
0.80 -0.0150 -0.0150 -0.0150 -0.0100 -0.0050 -0.0030 -0.0020 -0.0010 0.0000 0.0020 0.0030 0.0050 0.0100 0.0100 0.0050 0.0030 0.0000 0.0000
0.85 -0.0330 -0.0310 -0.0300 -0.0220 -0.0100 -0.0040 -0.0030 -0.0020 0.0000 0.0030 0.0060 0.0070 0.0080 0.0100 0.0100 0.0060 0.0040 0.0040
0.90 -0.0320 -0.0310 -0.0300 -0.0280 -0.0200 -0.0060 -0.0020 0.0000 0.0020 0.0040 0.0070 0.0070 0.0060 0.0160 0.0120 0.0120 0.0120 0.0120");
// ad = aero.Add("CM increment due speedbrakes", "CMBRK", "alpha");
// ad.AddFactor("fcs/speedbrake-pos-norm");
// ad.data = parse(ad, 1, @" -14 0
// -5 0.0219
// -3 0
// 0 0.0003
// 5 0.0000
// 8 -0.0180
// 12 -0.0220
// 14 0");
ad = aero.Add("CM increment due to gear", "CMUC", "alpha");
ad.AddFactor("gear/gear-pos-norm");
ad.data = parse(ad, 1, @"-10 0.00000
-4 0.00000
0 -0.01750
5 -0.01000
10 -0.00250
20 0.00000");
ad = aero.Add("CM increment due to flap mean position", "CMDFM", "alpha", "fcs/flap-pos-deg");
ad.data = parse(ad, 2, @" 0 5 10 15 20 60
0 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000
5 0.01320 0.00396 0.00589 0.00762 0.00798 0.00342
15 0.01520 0.00456 0.00649 0.01045 0.00798 0.00342
35 0.01696 0.01523 0.01355 0.01092 0.01148 0.01148");
// ad = aero.Add("Engine 0 EGT Rankine", "propulsion/engine[0]/EGT-R", "propulsion/engine[0]/n1");
// ad.AddComponent("atmosphere/T-R");
// ad.data = parse(ad, 1, @"
// 0.0 0.0
// 20.0 0.0
// 30.0 541.7
// 49.0 541.7
// 62.0 631.7
// 78.0 1171.7
// 95.0 1405.7
// 99.9 1684.7
// 104.0 1684.7");
// ad = aero.Add("Engine 1 EGT Rankine", "propulsion/engine[1]/EGT-R", "propulsion/engine[1]/n1");
// ad.AddComponent("atmosphere/T-R");
// ad.data = parse(ad, 1, @"
// 0.0 0.0
// 20.0 0.0
// 30.0 541.7
// 49.0 541.7
// 62.0 631.7
// 78.0 1171.7
// 95.0 1405.7
// 99.9 1684.7
// 104.0 1684.7");
ad = aero.Add("Cd increment due to ramps, NASA TP-3627, p14 Figure 10", "DCdRamp", "alpha");
ad.AddFactor("propulsion/inlet/ramp1-position-norm");
ad.data = parse(ad, 1, @" -5 -0.000497134
1.25 0.00100614
7.5 0.00670196
13.75 0.0126305
20 0.0163277
");
ad = aero.Add("CM increment due to ramps, NASA TP-3627, p14 Figure 10", "DCMRamp", "alpha");
ad.AddFactor("propulsion/inlet/ramp1-position-norm");
ad.data = parse(ad, 1, @"-5 -0.00197787
1.25 0.00134069
7.5 0.00981163
13.75 0.0215084
20 0.0319462
");
ad = aero.Add("Cl increment due to ramps, NASA TP-3627, p14 Figure 10", "DClRamp", "alpha");
ad.AddFactor("propulsion/inlet/ramp1-position-norm");
ad.data = parse(ad, 1, @"
-5 0.000055925
1.25 -0.000010545
7.5 0.000098660
13.75 0.000622195
20 0.001254030
");
}
public static void AddExtra(Aerodata aero)
{
var ad = aero.Add("Lift Mach factor (NASA-TM-84643 Figure 3 Clalpha) and values for AOA derived from NASA-aaia-2000-0900 Figure 4", "ClMach", "mach");
ad.data = parse(ad, 1, @"0 1
0.2 1
0.6 0.95837601
0.9 0.5
1.1 1
2.4 0.5
");
ad = aero.Add("Yaw factor (NASA-TM-84643 Figure 3 Clalpha) and values for AOA derived from NASA-aaia-2000-0900 Figure 4", "CyMach", "mach");
ad.data = parse(ad, 1, @"0 1
0.2 1
0.6 0.95837601
0.9 0.5
1.1 1
2.4 0.5
");
ad = aero.Add("Roll Mach factor (NASA-TM-84643 Figure 3 Clalpha) and values for AOA derived from NASA-aaia-2000-0900 Figure 4", "CLMach", "mach");
ad.data = parse(ad, 1, @"0 1
0.2 1
0.6 0.95837601
0.9 0.5
1.1 1
2.4 0.5
");
ad = aero.Add("Pitch Mach factor (NASA-TM-84643 Figure 3 Clalpha) and values for AOA derived from NASA-aaia-2000-0900 Figure 4", "CMMach", "mach");
ad.data = parse(ad, 1, @"0 1
0.2 1
0.6 0.95837601
0.9 0.5
1.1 1
2.4 0.5
");
ad = aero.Add("Yaw Mach factor (NASA-TM-84643 Figure 3 Clalpha) and values for AOA derived from NASA-aaia-2000-0900 Figure 4", "CNMach", "mach");
ad.data = parse(ad, 1, @"0 1
0.2 1
0.6 0.95837601
0.9 0.5
1.1 1
2.4 0.5
");
// var ad = aero.Add("Lift Mach factor (NASA-TM-84643 Figure 3 Clalpha) and values for AOA derived from NASA-aaia-2000-0900 Figure 4", "ClMach", "mach", "alpha");
// ad.data = parse(ad, 2, @" 0.0 0.2 0.6 0.9 1.1 1.3 1.5 1.8 2.1 2.6 3.0
// -20 1.00000000 1.00000000 0.96610485 1.23950808 1.41632259 1.34327421 1.13294356 0.93062904 0.76851372 0.58968226 0.51614275
// -15 1.00000000 1.00000000 0.96116198 1.23316641 1.40907629 1.33640164 1.12714710 0.92586768 0.76458179 0.58666528 0.51350202
// -10 1.00000000 1.00000000 0.99142346 1.27199174 1.45344001 1.37847726 1.16263449 0.95501794 0.78865408 0.60513601 0.52966925
// -5 1.00000000 1.00000000 0.96759116 1.24141501 1.41850155 1.34534078 1.13468655 0.93206078 0.76969605 0.59058947 0.51693681
// 4 1.00000000 1.00000000 0.95837601 1.22959201 1.40499202 1.33252801 1.12388001 0.92318401 0.76236561 0.58496481 0.51201361
// 8 1.00000000 1.00000000 0.99142346 1.27199174 1.45344001 1.37847726 1.16263449 0.95501794 0.78865408 0.60513601 0.52966925
// 12 1.00000000 1.00000000 0.96759116 1.24141501 1.41850155 1.34534078 1.13468655 0.93206078 0.76969605 0.59058947 0.51693681
// 16 1.00000000 1.00000000 0.98015728 1.25753729 1.43692365 1.36281274 1.14942274 0.94416546 0.77969210 0.59825946 0.52365028
// 20 1.00000000 1.00000000 0.96074823 1.23263556 1.40846972 1.33582635 1.12666189 0.92546912 0.76425265 0.58641274 0.51328097
// 24 1.00000000 1.00000000 0.96503140 1.23813085 1.41474891 1.34178168 1.13168474 0.92959501 0.76765981 0.58902706 0.51556926
// 28 1.00000000 1.00000000 0.96044147 1.23224199 1.40802001 1.33539984 1.12630217 0.92517363 0.76400864 0.58622551 0.51311708
// 32 1.00000000 1.00000000 0.96642959 1.23992472 1.41679867 1.34372573 1.13332438 0.93094186 0.76877204 0.58988048 0.51631624
// 40 1.00000000 1.00000000 0.95223257 1.22171001 1.39598566 1.32398617 1.11667565 0.91726616 0.75747865 0.58121503 0.50873147
// 45 1.00000000 1.00000000 0.95617790 1.22677185 1.40176956 1.32947176 1.12130231 0.92106662 0.76061706 0.58362314 0.51083926
// 50 1.00000000 1.00000000 0.95837601 1.22959201 1.40499202 1.33252801 1.12388001 0.92318401 0.76236561 0.58496481 0.51201361
//");
// ad = aero.Add("Sideforce Mach factor (NASA-TM-84643 Figure 3 Clalpha) and values for AOA derived from NASA-aaia-2000-0900 Figure 4", "CyMach", "mach", "alpha");
// ad.data = parse(ad, 2, @" 0.0 0.2 0.6 0.9 1.1 1.3 1.5 1.8 2.1 2.6 3.0
// -20 1.00000000 1.00000000 0.96610485 1.23950808 1.41632259 1.34327421 1.13294356 0.93062904 0.76851372 0.58968226 0.51614275
// -15 1.00000000 1.00000000 0.96116198 1.23316641 1.40907629 1.33640164 1.12714710 0.92586768 0.76458179 0.58666528 0.51350202
// -10 1.00000000 1.00000000 0.99142346 1.27199174 1.45344001 1.37847726 1.16263449 0.95501794 0.78865408 0.60513601 0.52966925
// -5 1.00000000 1.00000000 0.96759116 1.24141501 1.41850155 1.34534078 1.13468655 0.93206078 0.76969605 0.59058947 0.51693681
// 4 1.00000000 1.00000000 0.95837601 1.22959201 1.40499202 1.33252801 1.12388001 0.92318401 0.76236561 0.58496481 0.51201361
// 8 1.00000000 1.00000000 0.99142346 1.27199174 1.45344001 1.37847726 1.16263449 0.95501794 0.78865408 0.60513601 0.52966925
// 12 1.00000000 1.00000000 0.96759116 1.24141501 1.41850155 1.34534078 1.13468655 0.93206078 0.76969605 0.59058947 0.51693681
// 16 1.00000000 1.00000000 0.98015728 1.25753729 1.43692365 1.36281274 1.14942274 0.94416546 0.77969210 0.59825946 0.52365028
// 20 1.00000000 1.00000000 0.96074823 1.23263556 1.40846972 1.33582635 1.12666189 0.92546912 0.76425265 0.58641274 0.51328097
// 24 1.00000000 1.00000000 0.96503140 1.23813085 1.41474891 1.34178168 1.13168474 0.92959501 0.76765981 0.58902706 0.51556926
// 28 1.00000000 1.00000000 0.96044147 1.23224199 1.40802001 1.33539984 1.12630217 0.92517363 0.76400864 0.58622551 0.51311708
// 32 1.00000000 1.00000000 0.96642959 1.23992472 1.41679867 1.34372573 1.13332438 0.93094186 0.76877204 0.58988048 0.51631624
// 40 1.00000000 1.00000000 0.95223257 1.22171001 1.39598566 1.32398617 1.11667565 0.91726616 0.75747865 0.58121503 0.50873147
// 45 1.00000000 1.00000000 0.95617790 1.22677185 1.40176956 1.32947176 1.12130231 0.92106662 0.76061706 0.58362314 0.51083926
// 50 1.00000000 1.00000000 0.95837601 1.22959201 1.40499202 1.33252801 1.12388001 0.92318401 0.76236561 0.58496481 0.51201361
//");
// ad = aero.Add("Roll Mach factor (NASA-TM-84643 Figure 3 Clalpha) and values for AOA derived from NASA-aaia-2000-0900 Figure 4", "CLMach", "mach", "alpha");
// ad.data = parse(ad, 2, @" 0.0 0.2 0.6 0.9 1.1 1.3 1.5 1.8 2.1 2.6 3.0
// -20 1.00000000 1.00000000 0.96610485 1.23950808 1.41632259 1.34327421 1.13294356 0.93062904 0.76851372 0.58968226 0.51614275
// -15 1.00000000 1.00000000 0.96116198 1.23316641 1.40907629 1.33640164 1.12714710 0.92586768 0.76458179 0.58666528 0.51350202
// -10 1.00000000 1.00000000 0.99142346 1.27199174 1.45344001 1.37847726 1.16263449 0.95501794 0.78865408 0.60513601 0.52966925
// -5 1.00000000 1.00000000 0.96759116 1.24141501 1.41850155 1.34534078 1.13468655 0.93206078 0.76969605 0.59058947 0.51693681
// 4 1.00000000 1.00000000 0.95837601 1.22959201 1.40499202 1.33252801 1.12388001 0.92318401 0.76236561 0.58496481 0.51201361
// 8 1.00000000 1.00000000 0.99142346 1.27199174 1.45344001 1.37847726 1.16263449 0.95501794 0.78865408 0.60513601 0.52966925
// 12 1.00000000 1.00000000 0.96759116 1.24141501 1.41850155 1.34534078 1.13468655 0.93206078 0.76969605 0.59058947 0.51693681
// 16 1.00000000 1.00000000 0.98015728 1.25753729 1.43692365 1.36281274 1.14942274 0.94416546 0.77969210 0.59825946 0.52365028
// 20 1.00000000 1.00000000 0.96074823 1.23263556 1.40846972 1.33582635 1.12666189 0.92546912 0.76425265 0.58641274 0.51328097
// 24 1.00000000 1.00000000 0.96503140 1.23813085 1.41474891 1.34178168 1.13168474 0.92959501 0.76765981 0.58902706 0.51556926
// 28 1.00000000 1.00000000 0.96044147 1.23224199 1.40802001 1.33539984 1.12630217 0.92517363 0.76400864 0.58622551 0.51311708
// 32 1.00000000 1.00000000 0.96642959 1.23992472 1.41679867 1.34372573 1.13332438 0.93094186 0.76877204 0.58988048 0.51631624
// 40 1.00000000 1.00000000 0.95223257 1.22171001 1.39598566 1.32398617 1.11667565 0.91726616 0.75747865 0.58121503 0.50873147
// 45 1.00000000 1.00000000 0.95617790 1.22677185 1.40176956 1.32947176 1.12130231 0.92106662 0.76061706 0.58362314 0.51083926
// 50 1.00000000 1.00000000 0.95837601 1.22959201 1.40499202 1.33252801 1.12388001 0.92318401 0.76236561 0.58496481 0.51201361
//");
// ad = aero.Add("Pitch Mach factor (NASA-TM-84643 Figure 3 Clalpha) and values for AOA derived from NASA-aaia-2000-0900 Figure 4", "CMMach", "mach", "alpha");
// ad.data = parse(ad, 2, @" 0.0 0.2 0.6 0.9 1.1 1.3 1.5 1.8 2.1 2.6 3.0
// -20 1.00000000 1.00000000 0.96610485 1.23950808 1.41632259 1.34327421 1.13294356 0.93062904 0.76851372 0.58968226 0.51614275
// -15 1.00000000 1.00000000 0.96116198 1.23316641 1.40907629 1.33640164 1.12714710 0.92586768 0.76458179 0.58666528 0.51350202
// -10 1.00000000 1.00000000 0.99142346 1.27199174 1.45344001 1.37847726 1.16263449 0.95501794 0.78865408 0.60513601 0.52966925
// -5 1.00000000 1.00000000 0.96759116 1.24141501 1.41850155 1.34534078 1.13468655 0.93206078 0.76969605 0.59058947 0.51693681
// 4 1.00000000 1.00000000 0.95837601 1.22959201 1.40499202 1.33252801 1.12388001 0.92318401 0.76236561 0.58496481 0.51201361
// 8 1.00000000 1.00000000 0.99142346 1.27199174 1.45344001 1.37847726 1.16263449 0.95501794 0.78865408 0.60513601 0.52966925
// 12 1.00000000 1.00000000 0.96759116 1.24141501 1.41850155 1.34534078 1.13468655 0.93206078 0.76969605 0.59058947 0.51693681
// 16 1.00000000 1.00000000 0.98015728 1.25753729 1.43692365 1.36281274 1.14942274 0.94416546 0.77969210 0.59825946 0.52365028
// 20 1.00000000 1.00000000 0.96074823 1.23263556 1.40846972 1.33582635 1.12666189 0.92546912 0.76425265 0.58641274 0.51328097
// 24 1.00000000 1.00000000 0.96503140 1.23813085 1.41474891 1.34178168 1.13168474 0.92959501 0.76765981 0.58902706 0.51556926
// 28 1.00000000 1.00000000 0.96044147 1.23224199 1.40802001 1.33539984 1.12630217 0.92517363 0.76400864 0.58622551 0.51311708
// 32 1.00000000 1.00000000 0.96642959 1.23992472 1.41679867 1.34372573 1.13332438 0.93094186 0.76877204 0.58988048 0.51631624
// 40 1.00000000 1.00000000 0.95223257 1.22171001 1.39598566 1.32398617 1.11667565 0.91726616 0.75747865 0.58121503 0.50873147
// 45 1.00000000 1.00000000 0.95617790 1.22677185 1.40176956 1.32947176 1.12130231 0.92106662 0.76061706 0.58362314 0.51083926
// 50 1.00000000 1.00000000 0.95837601 1.22959201 1.40499202 1.33252801 1.12388001 0.92318401 0.76236561 0.58496481 0.51201361
//");
// ad = aero.Add("Yaw Mach factor (NASA-TM-84643 Figure 3 Clalpha) and values for AOA derived from NASA-aaia-2000-0900 Figure 4", "CNMach", "mach", "alpha");
// ad.data = parse(ad, 2, @" 0.0 0.2 0.6 0.9 1.1 1.3 1.5 1.8 2.1 2.6 3.0
// -20 1.00000000 1.00000000 0.96610485 1.23950808 1.41632259 1.34327421 1.13294356 0.93062904 0.76851372 0.58968226 0.51614275
// -15 1.00000000 1.00000000 0.96116198 1.23316641 1.40907629 1.33640164 1.12714710 0.92586768 0.76458179 0.58666528 0.51350202
// -10 1.00000000 1.00000000 0.99142346 1.27199174 1.45344001 1.37847726 1.16263449 0.95501794 0.78865408 0.60513601 0.52966925
// -5 1.00000000 1.00000000 0.96759116 1.24141501 1.41850155 1.34534078 1.13468655 0.93206078 0.76969605 0.59058947 0.51693681
// 4 1.00000000 1.00000000 0.95837601 1.22959201 1.40499202 1.33252801 1.12388001 0.92318401 0.76236561 0.58496481 0.51201361
// 8 1.00000000 1.00000000 0.99142346 1.27199174 1.45344001 1.37847726 1.16263449 0.95501794 0.78865408 0.60513601 0.52966925
// 12 1.00000000 1.00000000 0.96759116 1.24141501 1.41850155 1.34534078 1.13468655 0.93206078 0.76969605 0.59058947 0.51693681
// 16 1.00000000 1.00000000 0.98015728 1.25753729 1.43692365 1.36281274 1.14942274 0.94416546 0.77969210 0.59825946 0.52365028
// 20 1.00000000 1.00000000 0.96074823 1.23263556 1.40846972 1.33582635 1.12666189 0.92546912 0.76425265 0.58641274 0.51328097
// 24 1.00000000 1.00000000 0.96503140 1.23813085 1.41474891 1.34178168 1.13168474 0.92959501 0.76765981 0.58902706 0.51556926
// 28 1.00000000 1.00000000 0.96044147 1.23224199 1.40802001 1.33539984 1.12630217 0.92517363 0.76400864 0.58622551 0.51311708
// 32 1.00000000 1.00000000 0.96642959 1.23992472 1.41679867 1.34372573 1.13332438 0.93094186 0.76877204 0.58988048 0.51631624
// 40 1.00000000 1.00000000 0.95223257 1.22171001 1.39598566 1.32398617 1.11667565 0.91726616 0.75747865 0.58121503 0.50873147
// 45 1.00000000 1.00000000 0.95617790 1.22677185 1.40176956 1.32947176 1.12130231 0.92106662 0.76061706 0.58362314 0.51083926
// 50 1.00000000 1.00000000 0.95837601 1.22959201 1.40499202 1.33252801 1.12388001 0.92318401 0.76236561 0.58496481 0.51201361
//");
ad = aero.Add("Incremental Cd due to external tanks", "CdTNK", "mach");
ad.AddFactor("fcs/external-tanks-fitted");
ad.data = parse(ad, 1, @"0.4 0.0005
0.6 0.0005
0.7 0.0005
0.8 0.0005
0.85 0.0011
0.9 0.0065
0.94 0.0074
0.98 0.0077
1 0.0078
1.1 0.0079
1.2 0.0080
2 0.0081");
ad = aero.Add("Delta Cl due to mean flap position", "ClDFM", "alpha", "fcs/flap-pos-deg");
ad.data = parse(ad, 2, @" -20 -5 0 5 10 25 50
0 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000
10 -0.01400 -0.13160 0.13440 0.13160 0.12880 0.10920 0.01400
35 -0.09016 -0.25872 0.25480 0.25872 0.29872 0.21560 0.22540
50 -0.24500 -0.60200 0.59500 0.60200 0.58800 0.46200 0.24500
");
ad= aero.Add("Cl increment due to gear", "ClUC", "alpha");
ad.AddFactor("gear/gear-pos-norm");
ad.data = parse(ad, 1, @"-10 -0.00
0 -0.0012
8 -0.0010
12 -0.0004
14 -0.0002
16 -0.0001
18 -0.000");
ad= aero.Add("Cd increment due to gear", "CdUC", "alpha");
ad.AddFactor("gear/gear-pos-norm");
ad.data = parse(ad, 1, @" -10 0
-5 0.00017
0 0.00001
5 0.00005
10 0");
ad= aero.Add("Drag due to speedbrakes", "CdDBRK", "alpha");
ad.AddFactor("fcs/speedbrake-pos-norm");
ad.data = parse(ad, 1, @" -25 0.0210
-20 0.0210
-15 0.0414
-5 0.0650
0 0.0784
5 0.0650
15 0.0514
25 0.0210
40 0.0210");
ad= aero.Add("Drag increment due to mach (NASA-TP-2580 Figure 16)", "CdMach", "mach");
ad.data = parse(ad, 1, @"
0.20 0.0000000
0.80 0.0123600
0.84 0.0138600
0.90 0.0126000
0.94 0.0286800
0.98 0.0383800
0.99 0.0414400
1.00 0.0424750
1.03 0.0274150
1.20 0.0255100
1.25 0.0168750
1.70 0.0125000
2.00 -0.0063000
2.17 -0.0122500
2.47 -0.0130500");
ad = aero.Add("Delta Cd due to mean flap position", "CdDFM", "alpha", "fcs/flap-pos-deg");
ad.data = parse(ad, 2, @" -20 -5 0 5 10 25 50
0 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000
10 0.01400 0.02268 0.01932 0.02268 0.02548 0.02856 0.09590
35 0.09016 0.06894 0.06222 0.06894 0.09862 0.14286 0.55734");
ad = aero.Add("Pitch moment increment due to aim missiles", "DCMAIM", "alpha", "mach");
ad.AddFactor("fcs/aim-fitted");
ad.data = parse(ad, 2, @"-6 -5 -4 -3 -2 -1 0 1 2 3 4 5 6 7 8 9 10 20
0.80 -0.0150 -0.0150 -0.0150 -0.0100 -0.0050 -0.0030 -0.0020 -0.0010 0.0000 0.0020 0.0030 0.0050 0.0100 0.0100 0.0050 0.0030 0.0000 0.0000
0.85 -0.0330 -0.0310 -0.0300 -0.0220 -0.0100 -0.0040 -0.0030 -0.0020 0.0000 0.0030 0.0060 0.0070 0.0080 0.0100 0.0100 0.0060 0.0040 0.0040
0.90 -0.0320 -0.0310 -0.0300 -0.0280 -0.0200 -0.0060 -0.0020 0.0000 0.0020 0.0040 0.0070 0.0070 0.0060 0.0160 0.0120 0.0120 0.0120 0.0120");
// ad = aero.Add("CM increment due speedbrakes", "CMBRK", "alpha");
// ad.AddFactor("fcs/speedbrake-pos-norm");
// ad.data = parse(ad, 1, @" -14 0
// -5 0.0219
// -3 0
// 0 0.0003
// 5 0.0000
// 8 -0.0180
// 12 -0.0220
// 14 0");
ad = aero.Add("CM increment due to gear", "CMUC", "alpha");
ad.AddFactor("gear/gear-pos-norm");
ad.data = parse(ad, 1, @"-10 0.00000
-4 0.00000
0 -0.01750
5 -0.01000
10 -0.00250
20 0.00000");
ad = aero.Add("CM increment due to flap mean position", "CMDFM", "alpha", "fcs/flap-pos-deg");
ad.data = parse(ad, 2, @" 0 5 10 15 20 60
0 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000
5 0.01320 0.00396 0.00589 0.00762 0.00798 0.00342
15 0.01520 0.00456 0.00649 0.01045 0.00798 0.00342
35 0.01696 0.01523 0.01355 0.01092 0.01148 0.01148");
}