move data location

tests/aircraft/data/TO.yaml

@@ -0,0 +1,67 @@
+# Based on Twin-Otter Model
+name: TO
+mass: 4874.8
+ixx: 28366.4
+iyy: 32852.8
+izz: 52097.3
+ixz: 1384.3
+wing_area: 39.0
+wing_span: 19.8
+mac: 1.98
+
+# Drag coefficients
+c_D_0: 0.108
+c_D_alpha: 0.138
+c_D_alpha_q: -54.05
+c_D_alpha_deltae: 0.111
+c_D_alpha2: 2.988
+c_D_alpha2_q: 302.1
+c_D_alpha2_deltae: 0.156
+c_D_alpha3: -7.743
+c_D_alpha3_q: -218.8
+c_D_alpha4: 11.77
+
+# Side-force coefficients
+c_Y_beta: -0.885
+c_Y_p: -0.090
+c_Y_r: 1.697
+c_Y_deltaa: -0.051
+c_Y_deltar: -0.193
+
+# Lift coefficients
+c_L_0: 0.215
+c_L_alpha: 4.370
+c_L_q: 25.05
+c_L_deltae: 0.291
+c_L_alpha_q: 52.78
+c_L_alpha2: 16.62
+c_L_alpha3: -87.67
+c_L_alpha4: 90.41
+
+# Roll coefficients
+c_l_beta: -0.112
+c_l_p: -0.413
+c_l_r: 0.191
+c_l_deltaa: -0.206
+c_l_deltar: 0.116
+
+# Pitch coefficients
+c_m_0: 0.057
+c_m_alpha: -1.419
+c_m_q: -27.95
+c_m_deltae: -1.626
+c_m_alpha_q: 100.7
+c_m_alpha2_q: -759.2
+c_m_alpha2_deltae: 7.664
+c_m_alpha3_q: 1103.0
+c_m_alpha3_deltae: -8.121
+c_m_alpha4: 2.468
+
+# Yaw coefficients
+c_n_beta: 0.088
+c_n_p: -0.043
+c_n_r: -0.426
+c_n_deltaa: 0.023
+c_n_deltar: -0.087
+c_n_beta2: 0.337
+c_n_beta3: -0.766

tests/aircraft/data/f4.yaml

@@ -0,0 +1,68 @@
+# Based on F4 aircraft from Heffley and Jewell 1972
+name: F4Phantom
+mass: 17642.0
+ixx: 33898.0
+iyy: 165669.0
+izz: 189496.0
+ixz: 2952.0  # some deviation between Heffely & Jewell, Cook and GTM report on this
+wing_area: 49.239
+wing_span: 11.787
+mac: 4.889
+
+
+# Drag coefficients
+c_D_0: 0.031
+c_D_alpha: 0.280
+c_D_alpha_q: -11.98
+c_D_alpha_deltae: 0.0
+c_D_alpha2: -1.818
+c_D_alpha2_q: 209.4
+c_D_alpha2_deltae: 0.515
+c_D_alpha3: 22.27
+c_D_alpha3_q: -284.7
+c_D_alpha4: -29.81
+
+# Side-force coefficients
+c_Y_beta: -0.688
+c_Y_p: 0.129
+c_Y_r: 0.670
+c_Y_deltaa: 0.0
+c_Y_deltar: 0.089
+
+# Lift coefficients
+c_L_0: 0.105
+c_L_alpha: 1.519
+c_L_q: 6.727
+c_L_deltae: 0.265
+c_L_alpha_q: 33.25
+c_L_alpha2: 9.90
+c_L_alpha3: -12.71
+c_L_alpha4: -12.91
+
+# Roll coefficients
+c_l_beta: -0.034
+c_l_p: -0.236
+c_l_r: 0.025
+c_l_deltaa: -0.035
+c_l_deltar: 0.013
+
+# Pitch coefficients
+c_m_0: -0.013
+c_m_alpha: -0.254
+c_m_q: -2.916
+c_m_deltae: -0.403
+c_m_alpha_q: -3.955
+c_m_alpha2_q: -24.0
+c_m_alpha2_deltae: -0.270
+c_m_alpha3_q: 55.32
+c_m_alpha3_deltae: 1.479
+c_m_alpha4: -0.448
+
+# Yaw coefficients
+c_n_beta: 0.142
+c_n_p: -0.006
+c_n_r: -0.358
+c_n_deltaa: 0.001
+c_n_deltar: -0.053
+c_n_beta2: 0.0
+c_n_beta3: 0.377

tests/aircraft/data/gtm.yaml

@@ -0,0 +1,67 @@
+# Based on Generic Transport Model
+name: GTM
+mass: 22.5
+ixx: 67.2
+iyy: 5.77
+izz: 7.39
+ixz: 0.163
+wing_area: 0.548
+wing_span: 2.09
+mac: 0.279
+
+# Drag coefficients
+c_D_0: 0.019
+c_D_alpha: -0.078
+c_D_alpha_q: -27.42
+c_D_alpha_deltae: 0.293
+c_D_alpha2: 3.420
+c_D_alpha2_q: 288.2
+c_D_alpha2_deltae: -0.040
+c_D_alpha3: 1.819
+c_D_alpha3_q: 355.3
+c_D_alpha4: -6.563
+
+# Side-force coefficients
+c_Y_beta: -1.003
+c_Y_p: 0.033
+c_Y_r: 0.952
+c_Y_deltaa: -0.009
+c_Y_deltar: 0.253
+
+# Lift coefficients
+c_L_0: 0.016
+c_L_alpha: 5.343
+c_L_q: 30.78
+c_L_deltae: 0.396
+c_L_alpha_q: 12.03
+c_L_alpha2: 0.506
+c_L_alpha3: -36.30
+c_L_alpha4: 46.13
+
+# Roll coefficients
+c_l_beta: -0.109
+c_l_p: -0.366
+c_l_r: 0.061
+c_l_deltaa: -0.079
+c_l_deltar: 0.021
+
+# Pitch coefficients
+c_m_0: 0.182
+c_m_alpha: -1.782
+c_m_q: -44.34
+c_m_deltae: -1.785
+c_m_alpha_q: 374.0
+c_m_alpha2_q: -1748.0
+c_m_alpha2_deltae: 2.439
+c_m_alpha3_q: 1949.0
+c_m_alpha3_deltae: -0.038
+c_m_alpha4: 0.803
+
+# Yaw coefficients
+c_n_beta: 0.183
+c_n_p: -0.022
+c_n_r: -0.405
+c_n_deltaa: -0.009
+c_n_deltar: -0.129
+c_n_beta2: 0.184
+c_n_beta3: -0.377