applied most of GotGravel improvements

README.md

@@ -13,6 +13,7 @@ This mod is experimental. It has been made by gamers, not experts !
 * [Rotax 915 operators manual](http://www.aviagamma.ru/om915is-0-0.pdf)
 * [Additional manuals from rotax-owner.com](https://www.rotax-owner.com/en/support-topmenu/engine-manuals)
 * [Operating limitations from experimentalaircraft.info](https://www.experimentalaircraft.info/homebuilt-aircraft/rotax-aircraft-engines-3.php)
+* [Some more informations about the Rotax 915iS](https://www.kitplanes.com/more-rotax-915is/)
 
 ## Installation
 
@@ -48,7 +49,12 @@ After cloning this repo and making modifications, all you have to do is running
 
 ## Credits
 
-Thanks to [ryanbatc](https://forums.flightsimulator.com/u/ryanbatc) for this idea and creating the Rotax 914 engine mod.
+### Special thanks
+
+* [ryanbatc](https://forums.flightsimulator.com/u/ryanbatc) for this idea and creating the Rotax 914 engine mod.
+* [GotGravel](https://forums.flightsimulator.com/u/GotGravel) for multiples improvements on the mod.
+
+### Disclaimer
 
 No one here is affiliated with Rotax or JMB Aircraft. This addon is purely amateur and was created by fans of Flight Simulator 2020.
 

nanor-vl3rotax915/SimObjects/Airplanes/Asobo_VL3/engines.cfg

@@ -13,13 +13,13 @@ Engine.0 = 5.5, 0, 0
 ThrustAnglesPitchHeading.0 = 0, 0
 
 [PISTON_ENGINE]
-power_scalar = 1.8 ; Piston power scalar
+power_scalar = 1 ; Piston power scalar
 cylinder_displacement = 20.6 ; Cubic inches per cylinder
-compression_ratio = 11 ; Compression ratio
+compression_ratio = 8.3 ; Compression ratio
 number_of_cylinders = 4 ; Number of cylinders
 max_rated_rpm = 5800 ; Max rated RPM
 max_rated_hp = 141 ; Max rated HP
-min_cruise_rpm = 1400
+min_cruise_rpm = 1800
 max_cruise_rpm = 5500
 max_indicated_rpm = 7000
 min_required_rpm = 700 ; Minimum required RPM to prevent the engine from shutting down when applying ENGINE_POWER_IDLE
@@ -30,17 +30,17 @@ starter_time = 1.5 ; Time the Starter stays active when pressed
 turbocharged = 1 ; Is it turbocharged? 0=FALSE, 1=TRUE
 max_design_mp = 51 ; Max design manifold pressure, (inHg)
 min_design_mp = 1.7 ; Min design manifold pressure, (inHg)
-critical_altitude = 18000 ; Altitude to which the turbocharger will provide max design manifold pressure (feet)
+critical_altitude = 15000 ; Altitude to which the turbocharger will provide max design manifold pressure (feet)
 emergency_boost_type = 0 ; 0=None, 1=Water Injection, 2=Methanol/Water injection, 3=War Emergency Power
 emergency_boost_mp_offset = 0 ; Additional manifold pressure supplied by emergency boost
 emergency_boost_gain_offset = 0 ; Multiplier on manifold pressure due to emergency boost
 fuel_air_auto_mixture = 1 ; Automixture available? 0=FALSE, 1=TRUE
 auto_ignition = 0 ; Auto-Ignition available? 0=FALSE, 1=TRUE
-max_rpm_mechanical_efficiency_scalar = 0.92 ; Scalar on maximum RPM mechanical efficiency
+max_rpm_mechanical_efficiency_scalar = 1 ; Scalar on maximum RPM mechanical efficiency
 idle_rpm_mechanical_efficiency_scalar = 1
 max_rpm_friction_scalar = 0.24 ; Scalar on maximum RPM friction
 idle_rpm_friction_scalar = 0.24 ; Scalar on idle RPM friction
-BestPowerSpecificFuelConsumption = 0.49 ; SFC at Best Power mixture ratio
+BestPowerSpecificFuelConsumption = 0.42 ; SFC at Best Power mixture ratio
 egt_tuning_constant = 1
 egt_peak_temperature = 2100 ; typical peak EGT: 1200 degF + 460
 egt_tc = 0.05
@@ -60,7 +60,7 @@ radiator_temp_cooling_constant = 0.015
 radiator_temp_max = 670 ; max radiator temperature degrees Rankine
 radiator_temp_tc = 0.02
 fuel_press_tuning_constant = 1
-fuel_press_max = 2376 ; max fuel pressure (psf)
+fuel_press_max = 6480 ; max fuel pressure (psf)
 fuel_press_tc = 2
 number_of_magnetos = 2
 two_stroke_cycle = 0
@@ -91,9 +91,9 @@ egt_factor_from_pct_power = 0:0.5, 0.5:0.894, 0.64:0.956, 0.75:0.98, 1:1 ; Gives
 egt_delta_from_mixture_ratio = 0.043:-100, 0.05:-89.7, 0.067:-50, 0.07:0, 0.075:-4.9, 0.083:-80, 0.108:-120.5 ; Gives the EGT temperature delta (to current egt value after factor is applied) from the mixture ratio
 
 [PROPELLER]
-thrust_scalar = 1.30 ; Propeller thrust scalar
+thrust_scalar = 2.2 ; Propeller thrust scalar
 propeller_type = 0 ; 0=Constant Speed, 1=Fixed Pitch
-propeller_diameter = 6.1352 ; Propeller Diameter, (feet)
+propeller_diameter = 5.58 ; Propeller Diameter, (feet)
 propeller_blades = 3 ; Number of propeller blades
 propeller_moi = 2.83485 ; Propeller moment of inertia
 use_propeller_rpm = 0;

nanor-vl3rotax915/SimObjects/Airplanes/Asobo_VL3/flight_model.cfg

@@ -76,38 +76,38 @@ default_fuel_tank_selector.3 = 2 ; Default fuel selector used in case of autosta
 default_fuel_tank_selector.4 = 2 ; Default fuel selector used in case of autostart for engine 4, default is ALL.
 
 [AIRPLANE_GEOMETRY]
-wing_area = 105.2 ; Wing area S (SQUARE FEET)
+wing_area = 105.5 ; Wing area S (SQUARE FEET)
 wing_span = 27.69 ; Wing span b (FEET)
 wing_root_chord = 5 ; Wing root chord croot (FEET)
 wing_camber = 1 ; (DEGREES)
 wing_thickness_ratio = 0.03 ; Local thickness is local_chord(x)*wing_thickness_ratio, x = lateral coord
-wing_dihedral = 5 ; Dihedral angle Lambda (DEGREES)
+wing_dihedral = 7 ; Dihedral angle Lambda (DEGREES)
 wing_incidence = 0 ; Wing incidence (DEGREES)
 wing_twist = 0 ; Wing twist epsilon (DEGREES)
 oswald_efficiency_factor = 0.7 ; Wing Oswald efficiency factor e (non dimensional)
 wing_winglets_flag = 0 ; Has winglets true/false
-wing_sweep = 4 ; Wing sweep (DEGREES)
+wing_sweep = 2 ; Wing sweep (DEGREES)
 wing_pos_apex_lon = -7.41723 ; Longitudinal (z) position of wing apex w.r.t reference datum (FEET)
 wing_pos_apex_vert = -1.5 ; Vertical (y) position of wing apex w.r.t reference datum (FEET)
-htail_area = 14 ; Horizontal tail area (SQUARE FEET)
-htail_span = 8 ; Horizontal tail span (FEET)
+htail_area = 18.19 ; Horizontal tail area (SQUARE FEET)
+htail_span = 8.79 ; Horizontal tail span (FEET)
 htail_pos_lon = -11.5 ; Longitudinal (z) position of horizontal tail  w.r.t reference datum (FEET)
 htail_pos_vert = 0.5 ; Vertical (y) position of horizontal tail  w.r.t reference datum (FEET)
 htail_incidence = 0 ; Horizontal tail incidence (DEGREES)
-htail_sweep = 5 ; Horizontal tail sweep angle (DEGREES)
+htail_sweep = 3 ; Horizontal tail sweep angle (DEGREES)
 htail_thickness_ratio = 0.03 ; Local thickness is local_chord(x)*htail_thickness_ratio, x = lateral coord
-vtail_area = 13 ; Vertical tail area (SQUARE FEET)
+vtail_area = 9.43 ; Vertical tail area (SQUARE FEET)
 vtail_span = 4 ; Vertical tail span (FEET)
 vtail_sweep = 45 ; Vertical tail sweep angle (DEGREES)
 vtail_pos_lon = -10.75 ; Longitudinal (z) position of vertical tail  w.r.t reference datum (FEET)
 vtail_pos_vert = 1 ; Vertical (y) position of vertical tail  w.r.t reference datum (FEET)
 vtail_thickness_ratio = 0.03 ; Local thickness is local_chord(x)*vtail_thickness_ratio, x = lateral coord
-fuselage_length = 20 ; Nose to tail (FEET)
-fuselage_diameter = 3.4
+fuselage_length = 20.34 ; Nose to tail (FEET)
+fuselage_diameter = 3.77
 fuselage_center_pos = -2, 0, 0
-elevator_area = 7.16 ; Elevator area (SQUARE FEET)
-aileron_area = 7.04 ; Elevator area (SQUARE FEET)
-rudder_area = 10 ; Elevator area (SQUARE FEET)
+elevator_area = 7.86 ; Elevator area (SQUARE FEET)
+aileron_area = 2.23 ; Elevator area (SQUARE FEET)
+rudder_area = 3.33 ; Elevator area (SQUARE FEET)
 elevator_up_limit = 28 ; Elevator max deflection up angle (DEGREES)
 elevator_down_limit = 21 ; Elevator max deflection down angle (absolute value) (DEGREES)
 aileron_up_limit = 20 ; Aileron max deflection  angle (DEGREES)
@@ -235,7 +235,7 @@ induced_drag_scalar = 1
 flap_induced_drag_scalar = 1
 elevator_effectiveness = 1
 elevator_maxangle_scalar = 0.66
-aileron_effectiveness = 1
+aileron_effectiveness = 1.8
 rudder_effectiveness = 1
 rudder_maxangle_scalar = 0.5
 pitch_stability = 0.1
@@ -259,21 +259,21 @@ gyro_precession_on_pitch = 1
 [REFERENCE SPEEDS]
 full_flaps_stall_speed = 34 ; Knots True (KTAS)
 flaps_up_stall_speed = 44 ; Knots True (KTAS)
-cruise_speed = 200 ; Knots True (KTAS)
+cruise_speed = 205 ; Knots True (KTAS)
 max_mach = 0.3
-max_indicated_speed = 275 ; Red line (KIAS)
-max_flaps_extended = 64
+max_indicated_speed = 229 ; Red line (KIAS)
+max_flaps_extended = 65
 normal_operating_speed = 90
-airspeed_indicator_max = 275
+airspeed_indicator_max = 299
 rotation_speed_min = 38 ; Min speed required (Kts)
-climb_speed = 100 ; Climb speed (Kts)
-cruise_alt = 1500 ; (ft)
+climb_speed = 60 ; Climb speed (Kts)
+cruise_alt = 18000 ; (ft)
 takeoff_speed = 38 ; Takeoff Speed (Kts)
 spawn_cruise_altitude = 1500 ; Spawn Cruise Altitude (ft)
 spawn_descent_altitude = 500 ; Spawn Descent Altitude (ft)
-best_angle_climb_speed = 0 ; Best angle climb speed (Kts)
-approach_speed = 0 ; Approach speed (Kts)
-best_glide = 0 ; Best Glide (Kts)
+best_angle_climb_speed = 60 ; Best angle climb speed (Kts)
+approach_speed = 55 ; Approach speed (Kts)
+best_glide = 65 ; Best Glide (Kts)
 max_gear_extended = 300
 
 [INTERACTIVE POINTS]
@@ -295,6 +295,6 @@ pitch_scalar = 1 ; Scalar coefficient to ponderate global flap pitch coef (non d
 max_on_ground_position = 3 ; Dynamically set in-tool to last flap-position index by defaut when -1 is found.
 flaps-position.0 = 0, -1, 1, 0, 0, 0, 0
 flaps-position.1 = 15, -1, 0.33, 0, 0, 0, 0
-flaps-position.2 = 37, -1, 0.66, 0, 0, 0, 0
+flaps-position.2 = 38, -1, 0.66, 0, 0, 0, 0
 flaps-position.3 = 55, -1, 1, 0, 0, 0, 0
 

nanor-vl3rotax915/layout.json

@@ -7,13 +7,13 @@
     },
     {
       "path": "SimObjects/Airplanes/Asobo_VL3/engines.cfg",
-      "size": 11185,
-      "date": 132453422717710297
+      "size": 11178,
+      "date": 132457570950147274
     },
     {
       "path": "SimObjects/Airplanes/Asobo_VL3/flight_model.cfg",
-      "size": 16093,
-      "date": 132448038460882905
+      "size": 16112,
+      "date": 132457569781057985
     }
   ]
 }