public Gear(Aerodata a):base(a)
{
MaxSteer = new DenominatedAmount(0, "DEG");
dynamic_friction = new DenominatedAmount(0.5,null);
rolling_friction = new DenominatedAmount(0.02,null);
static_friction = new DenominatedAmount(0.8, null);
spring_coeff = new DenominatedAmount(a.EmptyWeight.Amount * 0.9, "LBS/FT");
damping_coeff = new DenominatedAmount(a.EmptyWeight.Amount * 0.05, "LBS/FT/SEC");
}
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 PointMassElement(Aerodata a)
{
}
public GroundReactionElement(Aerodata a)
{
spring_coeff = a.EmptyWeight;
spring_coeff = new DenominatedAmount(a.EmptyWeight.Amount * 0.9, "LBS/FT");
damping_coeff = new DenominatedAmount(a.EmptyWeight.Amount * 0.2, "LBS/FT/SEC");
}
private void OutputExtraIndependentVariables(Aerodata aero, HtmlTextWriter writer, DataElement aero_element)
{
foreach (var xx in aero_element.Factors)
{
var name = aero.Lookup(xx);
var v = aero.LookupValue(name);
if (v.HasValue)
{
// use the lookup value to find out if it is numeric; but lookup will add an xml comment for constants
// so output with the original name, rather than v
writer.Write(" <value>{0}</value>\n", name);
}
else
{
if (!name.Contains("/") && !Char.IsDigit(name[0]))
name = "aero/coefficients/" + name;
writer.Write(" <property>{0}</property>\n", name);
}
}
}
private void WriteFunctionDataToWriter(Aerodata aero, HtmlTextWriter writer, DataElement aero_element, DataElement aerodat_item)
{
if (aero.Is3d(aero_element))
{
writer.Write(" <function name=\"{0}\">\n", aerodat_item.GetVariable());
writer.Write(" <description>{0}</description>\n", aerodat_item.Title);
if (aero_element.Components.Any())
{
writer.Write(" <sum>\n");
foreach (var c in aero_element.Components)
writer.Write(" <property>{0}</property>\n", c);
}
writer.Write(" <product>\n");
OutputExtraIndependentVariables(aero, writer, aero_element);
writer.Write(" <table>\n");
writer.Write(" <independentVar lookup=\"row\">{0}</independentVar>\n", aero.Lookup(aero_element.IndependentVars[0]));
writer.Write(" <independentVar lookup=\"column\">{0}</independentVar>\n", aero.Lookup(aero_element.IndependentVars[1]));
writer.Write(" <independentVar lookup=\"table\">{0}</independentVar>\n", aero.Lookup(aero_element.IndependentVars[2]));
var table_data_element = aero_element.data.GroupBy(xx => xx.iv3).Select(xx => new { Key = xx.Key, Values = xx });
foreach (var table in table_data_element)
{
writer.Write(" <tableData breakPoint=\"{0}\">", table.Key);
var leading = " ";
var aero_data_element = table.Values.GroupBy(xx => xx.iv1).Select(xx => new { Key = xx.Key, Values = xx });
writer.Write("\n" + leading);
writer.Write("{0,6}", " ");
foreach (var iv2 in aero_data_element.First().Values)
{
writer.Write(FormatIntValue(iv2.iv2, 10));
}
foreach (var iv1 in aero_data_element)
{
writer.Write("\n" + leading);
writer.Write(FormatIntValue(iv1.Key, 6));
foreach (var vv in iv1.Values)
{
writer.Write(FormatValue(vv.Value, 10));
}
}
writer.Write("\n </tableData>\n");
}
writer.Write(" </table>\n");
writer.Write(" </product>\n");
if (aero_element.Components.Any())
{
writer.Write(" </sum>\n");
}
writer.Write(" </function>\n");
// writer.Write("<pre>\n");
}
else if (aero.Is2d(aero_element))
{
// writer.Write("<h2>{0}</h2>", aero_element);
// writer.Write("<pre>\n");
writer.Write(" <function name=\"{0}\">\n", aerodat_item.GetVariable());
writer.Write(" <description>{0}</description>\n", aerodat_item.Title);
if (aero_element.Components.Any())
{
writer.Write(" <sum>\n");
foreach (var c in aero_element.Components)
writer.Write(" <property>{0}</property>\n", c);
}
writer.Write(" <product>\n");
OutputExtraIndependentVariables(aero, writer, aero_element);
writer.Write(" <table>\n");
writer.Write(" <independentVar lookup=\"row\">{0}</independentVar>\n", aero.Lookup(aero_element.IndependentVars[0]));
writer.Write(" <independentVar lookup=\"column\">{0}</independentVar>\n", aero.Lookup(aero_element.IndependentVars[1]));
writer.Write(" <tableData>");
var leading = " ";
var aero_data_element = aero_element.data.GroupBy(xx => xx.iv1).Select(xx => new { Key = xx.Key, Values = xx });
writer.Write("\n" + leading);
writer.Write(" ");
foreach (var iv2 in aero_data_element.First().Values)
{
writer.Write(" {0,10}\t", iv2.iv2);
}
foreach (var iv1 in aero_data_element)
{
writer.Write("\n{0}{1}", leading, FormatIntValue(iv1.Key, 6));
foreach (var vv in iv1.Values)
{
writer.Write(FormatValue(vv.Value, 10));
}
}
writer.Write("\n </tableData>\n");
writer.Write(" </table>\n");
writer.Write(" </product>\n");
if (aero_element.Components.Any())
{
writer.Write(" </sum>\n");
}
writer.Write(" </function>\n");
// writer.Write("<pre>\n");
}
else if (aero_element.IndependentVars.Count == 1)
{
var aero_data_element = aero_element.data.Select(xx => new { Key = xx.iv1, Value = xx.Value });
if (aero_data_element != null)
if (aero_data_element != null)
{
// writer.Write("<h2>{0}</h2>", aero_element);
// writer.Write("<pre>\n");
writer.Write(" <function name=\"{0}\">\n", aerodat_item.GetVariable());
writer.Write(" <description>{0}</description>\n", aero_element.Title);
if (aero_element.Components.Any())
{
writer.Write(" <sum>\n");
foreach (var c in aero_element.Components)
writer.Write(" <property>{0}</property>\n", c);
}
writer.Write(" <product>\n");
OutputExtraIndependentVariables(aero, writer, aero_element);
writer.Write(" <table>\n");
writer.Write(" <independentVar lookup=\"row\">{0}</independentVar>\n", aero.Lookup(aero_element.IndependentVars[0]));
writer.Write(" <tableData>\n");
var leading = " ";
foreach (var q in aero_data_element)
{
writer.Write("{0}{1}\t{2}\n", leading, FormatIntValue(q.Key, 6), FormatValue(q.Value, 10));
}
writer.Write(" </tableData>\n");
writer.Write(" </table>\n");
writer.Write(" </product>\n");
if (aero_element.Components.Any())
{
writer.Write(" </sum>\n");
}
writer.Write(" </function>\n");
// writer.Write("<pre>\n");
}
}
else
{
writer.Write(" <!-- cannot handle {0} -->", aero_element.Variable);
}
if (!aero.IsUsed(aero_element))
writer.Write(" -->\n");
}
public string GetComputeValue(Aerodata aero)
{
var vals = new List<String>();
vals.Add(Variable);
foreach (var xx in Factors)
{
if (aero != null)
{
var name = aero.Lookup(xx);
var v = aero.LookupValue(xx);
if (v.HasValue)
{
vals.Add(v.ToString());
}
else
{
vals.Add(xx);
}
}
else
vals.Add(xx);
}
return string.Join("*", vals);
}
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");
}
