Improved engine performance and flight dynamics

.github/CHANGELOG.md

@@ -4,6 +4,10 @@
 <!-- Use the following format below -->
 <!--  1. [Changed Area] Title of changes - @github username (Name)  -->
 ## 2020/10
+1. [CDU] Added actual VLS and VApp calculation - @MisterChocker (Leon)
+1. [PFD] Added actual F and S speed calculation for approach - @MisterChocker (Leon)
+1. [ENGINE] Improved engine performance - @MisterChocker (Leon)
+1. [AERODYNAMICS] Improved overall flight performance - @MisterChocker (Leon)
 1. [ND] Change ND Sizing - @nathaninnes (Nathan Innes)
 1. [GPWS] Added Pull Up, Sink Rate, Dont sink GPWS with Default Sounds & Added (Too low) terrain, flaps and gear without Sounds (Future PR by Boris) - @oliverpope03 (Oliver Pope)
 1. [Sounds] Added new sounds for fuel pumps, flaps, ground roll and rattles, touchdowns, and wind - @hotshotp (Boris)

A32NX/SimObjects/AirPlanes/Asobo_A320_NEO/engines.cfg

@@ -28,7 +28,7 @@ AfterBurnThrustSpecificFuelConsumption = 0.011
 mach_0_corrected_commanded_ne_table = 0.000000:1.000000:22.570000,0.000000:66.000000:82.500000,0.420000:78.800003:95.400002,0.510000:82.500000:98.500000,0.610000:87.400002:101.099998,0.700000:92.000000:103.099998,0.790000:96.199997:105.699997,0.930000:103.099998:108.059998,1.000000:105.000000:108.059998
 mach_hi_corrected_commanded_ne_table = 0.900000:1.000000:22.570000,0.000000:62.000000:82.500000,0.420000:77.000000:95.400002,0.510000:80.199997:98.500000,0.610000:84.800003:101.099998,0.700000:89.099998:103.099998,0.790000:92.199997:105.699997,0.930000:96.000000:108.059998,1.000000:98.199997:108.059998
 corrected_n2_from_ff_table = 0.000000:0.000000, 0.002940:10.000000, 0.011800:30.000000, 0.020660:40.000000, 0.033970:50.000000, 0.053170:60.000000, 0.133910:80.000000, 0.257710:90.000000, 0.540000:100.000000, 0.686860:105.000000
-n1_and_mach_on_thrust_table = 0.000000:0.000000:0.100000:0.200000:0.300000:0.400000:0.500000:0.600000:0.700000:0.800000:0.900000,0.000000:0.000000:0.000000:0.000000:0.000000:0.000000:0.000000:0.000000:0.000000:0.000000:0.000000,20.000000:0.016000:0.017000:0.018000:0.019000:0.020000:0.021000:0.022000:0.023000:0.024000:0.025000,25.000000:0.032000:0.034000:0.036000:0.038000:0.040000:0.042000:0.044000:0.046000:0.048000:0.050000,30.000000:0.053000:0.056000:0.059000:0.062000:0.065000:0.068000:0.071000:0.074000:0.077000:0.080000,35.000000:0.084000:0.088000:0.092000:0.096000:0.100000:0.104000:0.108000:0.112000:0.116000:0.120000,40.000000:0.136000:0.142000:0.148000:0.154000:0.160000:0.166000:0.172000:0.178000:0.184000:0.190000,45.000000:0.209000:0.217000:0.225000:0.233000:0.241000:0.249000:0.257000:0.265000:0.273000:0.281000,50.000000:0.310000:0.320000:0.330000:0.340000:0.350000:0.360000:0.370000:0.380000:0.390000:0.400000,55.000000:0.423000:0.435000:0.446000:0.458000:0.470000:0.482000:0.494000:0.505000:0.517000:0.529000,60.000000:0.536000:0.551000:0.565000:0.579000:0.594000:0.608000:0.622000:0.636000:0.651000:0.665000,65.000000:0.618000:0.636000:0.653000:0.671000:0.688000:0.705000:0.723000:0.740000:0.758000:0.775000,70.000000:0.700000:0.721000:0.742000:0.763000:0.784000:0.805000:0.826000:0.847000:0.868000:0.889000,75.000000:0.772000:0.797000:0.822000:0.847000:0.872000:0.897000:0.922000:0.947000:0.972000:0.997000,80.000000:0.838000:0.868000:0.898000:0.928000:0.958000:0.988000:1.018000:1.048000:1.078000:1.108000,85.000000:0.889000:0.924000:0.959000:0.994000:1.029000:1.064000:1.099000:1.134000:1.169000:1.204000,90.000000:0.923000:0.963000:1.003000:1.043000:1.083000:1.123000:1.163000:1.203000:1.243000:1.283000,95.000000:0.964000:1.008000:1.052000:1.096000:1.140000:1.184000:1.228000:1.272000:1.316000:1.360000,100.000000:1.000000:1.038000:1.086000:1.134000:1.182000:1.230000:1.278000:1.326000:1.374000:1.422000,105.000000:1.016000:1.067000:1.118000:1.169000:1.220000:1.271000:1.322000:1.373000:1.424000:1.475000,110.000000:1.032000:1.084000:1.136000:1.188000:1.240000:1.292000:1.344000:1.396000:1.448000:1.500000
+n1_and_mach_on_thrust_table = 0.000000:0.000000:0.100000:0.200000:0.300000:0.400000:0.500000:0.600000:0.700000:0.800000:0.900000,0.000000:0.000000:0.000000:0.000000:0.000000:0.000000:0.000000:0.000000:0.000000:0.000000:0.000000,20.000000:0.105605:0.105605:0.105605:0.105605:0.127396:0.134235:0.141209:0.141209:0.141209:0.141209,25.000000:0.130304:0.136232:0.142160:0.148089:0.156070:0.164210:0.172508:0.172508:0.172508:0.172508,30.000000:0.163064:0.170258:0.177452:0.184646:0.194398:0.204342:0.214477:0.214477:0.214477:0.214477,35.000000:0.193653:0.201151:0.208648:0.216146:0.226625:0.237304:0.248184:0.248184:0.248184:0.248184,40.000000:0.229135:0.237151:0.245168:0.253185:0.264684:0.276397:0.281671:0.281671:0.281671:0.281671,45.000000:0.272800:0.281600:0.290400:0.299200:0.312107:0.325248:0.330810:0.330810:0.330810:0.330810,50.000000:0.326841:0.336741:0.346361:0.355981:0.370760:0.385515:0.391283:0.391283:0.391283:0.391283,55.000000:0.389066:0.400331:0.411034:0.421738:0.438776:0.455539:0.461681:0.461681:0.461681:0.461681,60.000000:0.465248:0.478268:0.490420:0.502572:0.522467:0.541817:0.548534:0.548534:0.548534:0.548534,65.000000:0.545076:0.560952:0.575946:0.591822:0.614907:0.638392:0.647889:0.647889:0.647889:0.647889,70.000000:0.633062:0.652675:0.671847:0.691460:0.720107:0.749265:0.761408:0.761408:0.761408:0.761408,75.000000:0.721048:0.744398:0.767748:0.791098:0.825307:0.860139:0.874926:0.874926:0.874926:0.874926,80.000000:0.805318:0.834148:0.862978:0.891808:0.932913:0.974787:0.993951:0.993951:0.993951:0.993951,85.000000:0.880570:0.912094:0.943618:0.975142:1.020089:1.065875:1.086830:1.086830:1.086830:1.086830,90.000000:0.945767:0.979625:1.013483:1.047341:1.095615:1.144792:1.194871:1.230084:1.265296:1.300508,95.000000:0.981930:1.026749:1.071567:1.116386:1.176687:1.238183:1.300874:1.347486:1.394097:1.440708,100.000000:1.005186:1.051066:1.096946:1.142826:1.204555:1.267507:1.331684:1.379399:1.427114:1.474829,105.000000:1.018622:1.065115:1.111608:1.158102:1.220656:1.284450:1.349484:1.397837:1.446190:1.494543,110.000000:1.021840:1.068480:1.115120:1.161760:1.224512:1.288508:1.353747:1.402253:1.450758:1.499264
 n2_to_n1_table = 0.000000:0.000000:0.900000,0.000000:0.000000:0.000000,10.000000:2.000000:9.200000,20.000000:7.000000:14.600000,30.000000:10.200000:20.000000,40.000000:15.100000:24.700001,50.000000:20.100000:32.000000,60.000000:28.000000:41.799999,70.000000:38.000000:53.200001,80.000000:52.000000:67.500000,90.000000:70.000000:80.800003,100.000000:89.400002:100.800003,110.000000:112.000000:120.000000
 corrected_airflow_table = 0.000000:0.000000:0.100000:0.200000:0.300000:0.400000:0.500000:0.600000:0.700000:0.800000:0.900000,0.000000:0.000000:0.000000:0.000000:0.000000:0.000000:0.000000:0.000000:0.000000:0.000000:0.000000,20.000000:2.783298:3.327631:4.346876:5.190300:5.839087:6.246526:6.700677:7.411100:8.091678:9.135577,25.000000:3.932301:4.355959:5.384287:6.293239:6.812269:7.184673:7.638175:8.288260:8.893579:9.831077,30.000000:5.067030:5.414781:6.261448:7.274854:7.743927:8.182508:8.651582:9.195914:9.770740:10.587564,35.000000:6.216682:6.473602:7.169102:8.000848:8.530258:9.105083:9.619573:10.118490:10.618056:11.358972,40.000000:7.350762:7.532423:8.061833:8.848164:9.437912:10.073075:10.602486:10.995650:11.449802:12.084965,45.000000:8.530258:8.591244:9.090161:9.725325:10.345566:11.041066:11.570477:11.903304:12.326962:12.841451,50.000000:9.650065:9.679910:10.118490:10.678393:11.283064:12.009057:12.554038:12.780465:13.173631:13.567445,55.000000:10.784146:10.784146:11.177311:11.631462:12.266625:12.962126:13.522029:13.703041:14.006024:14.262944,60.000000:11.933798:11.948720:12.372377:12.689635:13.294953:13.899624:14.610695:14.580202:14.883185:15.019431,65.000000:12.992619:13.083448:13.476614:13.793871:14.277866:14.867615:15.230935:15.458011:15.729853:15.714931,70.000000:14.172114:14.262944:14.625617:14.898108:15.291273:15.790839:16.093174:16.335173:16.561598:16.440924,75.000000:15.351610:15.472933:15.729853:16.047758:16.350094:16.743259:17.076088:17.257748:17.212332:17.121502,80.000000:16.622585:16.713415:16.955412:17.181839:17.439407:17.832573:18.074572:18.165401:18.059000:18.013586,85.000000:18.059000:18.074572:18.286076:18.452814:18.618904:18.830408:19.087976:19.042562:18.966654:18.921238,90.000000:19.632311:19.652422:19.672535:19.693296:19.713408:19.733521:19.753633:19.774395:19.794506:19.814619,95.000000:20.842299:20.862411:20.882523:20.903284:20.923397:20.943510:20.963621:20.984383:21.004496:21.024609,100.000000:21.795368:21.815479:21.835592:21.855705:21.876467:21.896578:21.916691:21.936804:21.957565:21.977676,105.000000:22.521360:22.541473:22.561586:22.581697:22.602459:22.622572:22.642685:22.662796:22.683558:22.703671,110.000000:22.898954:22.919716:22.939829:22.959942:22.980053:23.000814:23.020927:23.041040:23.061152:23.081913
 epr_max = 1.4
@@ -78,10 +78,10 @@ low_idle_n1 = 19.5
 low_idle_n2 = 58.5
 high_n1 = 92.4
 high_n2 = 95.2
-high_fuel_flow = 6212
+high_fuel_flow = 2672.226673
 min_n2_for_fuel_flow = 22
 mach_influence_on_n1 = 10
-fuel_flow_max = 6323
+fuel_flow_max = 2720.166113
 fuel_flow_controller_p = 0.5
 fuel_flow_controller_i = 0.01
 fuel_flow_controller_d = 0.1
@@ -100,4 +100,3 @@ DisableFuelValveControls = 1 ; Disable fuel valve controls
 DisableMixtureControls = 1 ; Disable mixture controls
 DisableParkingBrakeControls = 0 ; Disable parking brake controls
 DisablePropellerControls = 0 ; Disable propeller controls
-

A32NX/SimObjects/AirPlanes/Asobo_A320_NEO/flight_model.cfg

@@ -209,23 +209,23 @@ lift_coef_pitch_rate = -39.21729 ; The change in lift per change in pitch rate
 lift_coef_daoa = 0 ; lift per change in angle of attack rate
 lift_coef_delta_elevator = -1.32794 ; The change in lift per change in elevator deflection
 lift_coef_horizontal_incidence = 0 ; The change in lift per change in horizontal incidence angle
-lift_coef_flaps = 1.4538 ; Change in lift due to flaps
-lift_coef_spoilers = -0.3 ; Change in lift due to spoilers
+lift_coef_flaps = 1.5038 ; Change in lift due to flaps
+lift_coef_spoilers = -0.1 ; Change in lift due to spoilers
 drag_coef_zero_lift = 0.0237 ; The zero lift drag polar
-drag_coef_flaps = 0.1566
-drag_coef_gear = 0.005
-drag_coef_spoilers = 0.15
+drag_coef_flaps = 0.046
+drag_coef_gear = 0.03
+drag_coef_spoilers = 0.035
 side_force_slip_angle = -3.53325 ; (yaw angle) The change in side force per change in side slip angle
 side_force_roll_rate = 1.59695 ; (roll velocity)  The change in side force per change in roll rate
 side_force_yaw_rate = 14.29526 ; (yaw velocity) The change in side force per change in yaw rate
 side_force_delta_rudder = -3.07387 ; The change in side force per change in rudder deflection
 pitch_moment_horizontal_incidence = 0 ; The change in pitch moment per change in horizontal incidence angle
-pitch_moment_delta_elevator = -6.51784 ; The change in pitch moment per change in elevator deflection
+pitch_moment_delta_elevator = -12.51784 ; The change in pitch moment per change in elevator deflection
 pitch_moment_delta_trim = -6.51784 ; The change in pitch moment per change in trim
 pitch_moment_pitch_damping = -1020.74249 ; The change in pitch moment per change in pitch rate(PRIMARY PITCH STABILITY FACTOR). deg/s
 pitch_moment_aoa_0 = -0.28489 ; Pitch moment at zero angle - of - attack
 pitch_moment_daoa = 0 ; The change in pitch moment per change in angle of attack
-pitch_moment_flaps = -0.6355 ; The pitch moment due to flaps
+pitch_moment_flaps = -0.6335 ; The pitch moment due to flaps
 pitch_moment_gear = 0.00242 ; The pitch moment due to gear
 pitch_moment_spoilers = 0.01028 ; The pitch moment due to spoilers
 pitch_moment_delta_elevator_propwash = -1.62946
@@ -248,7 +248,7 @@ yaw_moment_delta_rudder_trim_scalar = 1.31766 ; Change in yaw moment due to rudd
 compute_aero_center = 0
 aero_center_lift = -8.75 ; Init to center
 lift_coef_aoa_table = -3.15:0, -0.5:-1.389, 0:0.3, 0.2:1.086, 0.23:1.188, 0.26:1.2233, 0.29:1.20, 0.31:1.183, 0.4:1.15, 0.8:1.421, 3.15:0
-lift_coef_ground_effect_mach_table = 0.054:1.25
+lift_coef_ground_effect_mach_table = 0.027:1.25
 lift_coef_mach_table = 0:1
 lift_coef_delta_elevator_mach_table = 0:0
 lift_coef_daoa_mach_table = 0:0
@@ -295,7 +295,7 @@ lift_coef_at_drag_zero = 0.10000
 lift_coef_at_drag_zero_flaps = 0.10000
 
 [FLIGHT_TUNING]
-cruise_lift_scalar = 1
+cruise_lift_scalar = 1.2
 parasite_drag_scalar = 1
 induced_drag_scalar = 1
 flap_induced_drag_scalar = 1
@@ -324,8 +324,8 @@ wingflex_scalar = 0.75
 wingflex_offset = -0.25
 
 [REFERENCE SPEEDS]
-full_flaps_stall_speed = 121 ; Knots True (KTAS)
-flaps_up_stall_speed = 179 ; Knots True (KTAS)
+full_flaps_stall_speed = 110 ; Knots True (KTAS)
+flaps_up_stall_speed = 166 ; Knots True (KTAS)
 cruise_speed = 455 ; Knots True (KTAS)
 cruise_mach = 0.78
 crossover_speed = 320 ; Knots Indicated (KIAS)
@@ -334,10 +334,10 @@ max_indicated_speed = 500 ; Red line (KIAS)
 max_flaps_extended = 274.030126
 normal_operating_speed = 350 ; VMO
 airspeed_indicator_max = 562.5
-rotation_speed_min = 145 ; Min speed required (Kts)
+rotation_speed_min = 120 ; Min speed required (Kts)
 climb_speed = 231 ; Climb speed (Kts)
 cruise_alt = 36000 ; (ft)
-takeoff_speed = 150 ; Takeoff Speed (Kts)
+takeoff_speed = 115 ; Takeoff Speed (Kts)
 spawn_cruise_altitude = 5000 ; Spawn Cruise Altitude (ft)
 spawn_descent_altitude = 500 ; Spawn Descent Altitude (ft)
 best_angle_climb_speed = 0 ; Best angle climb speed (Kts)
@@ -376,16 +376,16 @@ extending-time = 12 ; Flap extension time (SECONDS)
 damaging-speed = 233 ; Speed above which flap is damaged (Kts)
 blowout-speed = 250 ; Speed above which flap is blown out (Kts)
 maneuvering_flaps = 0
-lift_scalar = 0.1 ; Scalar coefficient to ponderate global flap lift coef (non dimensioned)
-drag_scalar = 0.1 ; Scalar coefficient to ponderate global flap drag coef (non dimensioned)
+lift_scalar = 1.4 ; Scalar coefficient to ponderate global flap lift coef (non dimensioned)
+drag_scalar = 1 ; Scalar coefficient to ponderate global flap drag coef (non dimensioned)
 pitch_scalar = 1 ; Scalar coefficient to ponderate global flap pitch coef (non dimensioned)
 max_on_ground_position = 4 ; Dynamically set in-tool to last flap-position index by defaut when -1 is found.
 flaps-position.0 = 0, -1, 0
-flaps-position.1 = 10, 215, 0.25
+flaps-position.1 = 10, 230, 0.5857
 flaps-position-autoretract.1 = 0, 210, 230
 flaps-position-inhibit.1 = air,increasing
-flaps-position.2 = 15, 200, 0.5
-flaps-position.3 = 20, 185, 0.75
+flaps-position.2 = 15, 200, 0.8286
+flaps-position.3 = 20, 185, 0.8967
 flaps-position.4 = 35, 177, 1
 
 [FLAPS.1]
@@ -396,12 +396,12 @@ extending-time = 12 ; Flap extension time (SECONDS)
 damaging-speed = 260 ; Speed above which flap is damaged (Kts)
 blowout-speed = 270 ; Speed above which flap is blown out (Kts)
 maneuvering_flaps = 0
-lift_scalar = 2.0 ; Scalar coefficient to ponderate global flap lift coef (non dimensioned)
-drag_scalar = 2.0 ; Scalar coefficient to ponderate global flap drag coef (non dimensioned)
+lift_scalar = 0.55 ; Scalar coefficient to ponderate global flap lift coef (non dimensioned)
+drag_scalar = 1.85 ; Scalar coefficient to ponderate global flap drag coef (non dimensioned)
 pitch_scalar = 1 ; Scalar coefficient to ponderate global flap pitch coef (non dimensioned)
 max_on_ground_position = 4 ; Dynamically set in-tool to last flap-position index by defaut when -1 is found.
 flaps-position.0 = 0, -1, 0
-flaps-position.1 = 18, 215, 0.25
-flaps-position.2 = 22, 200, 0.5
-flaps-position.3 = 22, 185, 0.75
+flaps-position.1 = 18, 230, 0.6667
+flaps-position.2 = 22, 200, 0.8848
+flaps-position.3 = 22, 185, 0.8848
 flaps-position.4 = 27, 177, 1