il2_specs

P-38J-25

Description

Vitesse de décrochage indiquée en configuration de vol : 179..220 km/h (111..138 mph)
Vitesse de décrochage indiquée en configuration de décollage/atterrissage : 149..185 km/h (93..115 mph)

Vitesse limite de piqué : 725 km/h (450 mph)
Facteur de charge maximum : 9,0 g
Angle d\attaque de décrochage en configuration de vol : 14,1 °
Angle d\attaque de décrochage indiquée en configuration d\atterrissage : 11,5 °

Vitesse sol au niveau de la mer, régime moteur - Urgence: 557 km/h (346 mph)
Vitesse sol maximale à 7860 m (25800 feet), régime moteur - Urgence: 674 km/h (419 mph)

Vitesse sol au niveau de la mer, régime moteur - Combat: 540 km/h (336 mph)
Vitesse sol maximale à 9000 m (27890 feet), régime moteur - Combat: 670 km/h (416 mph)

Plafond opérationnel : 12350 m (40500 feet)

Régime moteur - Urgence
Taux de montée au niveau de la mer: 20.4 m/s (4020 feet/min)
Taux de montée à 3000 m (9843 feet): 19.1 m/s (3758 feet/min)
Taux de montée à 6000 m (19685 feet): 15.0 m/s (2953 feet/min)

Régime moteur - Combat
Taux de montée au niveau de la mer: 12.8 m/s (2518 feet/min)
Taux de montée à 3000 m (9843 feet): 11.5 m/s (2258 feet/min)
Taux de montée à 6000 m (19685 feet): 9.4 m/s (1844 feet/min)

Virage à 360° au niveau de la mer en: 20,0 s, à 310 km/h (195 mph) vitesse indiquée (IAS).
Virage à 360° à 3000 m (9843 feet): 28,3 s, à 320 km/h (200 mph) vitesse indiquée (IAS).

Endurance à 3000 m (9843 feet): 5,8 h, à 350 km/h (217 mph) vitesse indiquée (IAS).

Vitesse de décollage : 160..175 km/h (100..110 mph)
Vitesse d\approche : 185..210 km/h (115..130 mph)
Vitesse d\atterrissage : 150..175 km/h (95..110 mph)
Angle d\atterrissage : 7,0 °

Note 1 : les données sont indiquées à l\atmosphère standard international (ISA).
Note 2 : les performances d\endurance sont données pour plusieurs masses possibles.
Note 3 : la vitesse maximale, le taux de montée et le temps de virage sont donnés pour une masse standard et 70% 25 de carburant.
Note 4 : le temps de virage est à régime Urgence.

Moteur :
Modèle : Allison V-1710-89 (gauche) et V-1710-91 (droite)
Puissance maximale àu régime de Urgence au niveau de la mer: 1550 cv
Puissance maximale au régime de Urgence à 7860 m (25800 feet): 1505 cv

Performance du moteur :
Continu (durée illimitée) : 2600 tr/min, 44 inch Hg
Combat (jusqu\à 15 minutes) : 3000 tr/min, 54 inch Hg
Urgence (jusqu\à 5 minute) : 3000 tr/min, 60 inch Hg

Régime de turbocompresseur maximal en continu: 24000
Régime maximal du turbocompresseur jusquà 15 minutes: 26400

Température de fonctionnement d\eau en sortie du moteur : 85 °C
Température maximale d\eau en sortie du moteur : 105 °C
Température de fonctionnement d\huile en sortie du moteur : 105 °C
Température maximale d\huile en sortie du moteur : 115 °C

Altitude de changement d\étage du compresseur : étage simple

Masse à vide : 6356 kg (14013 lb)
Masse minimale (sans munitions, 10% de carburant) : 6662 kg (14687 lb)
Masse standard : 7890 kg (17395 lb)
Masse maximale au décollage : 10113 kg (22295 lb)
Masse de carburant : 1132 kg (2496 lb) / 1575 l (416 gal)
Charge utile : 3757 kg (8282 lb)

Armement offensif :
canon M2 de 20 mm, 150 coups, 650 coups par minute, dans le nez
4 mitrailleuse M2 de 12,7 mm, 300 coups, 850 coups par minute, dans le nez
Il est possible de d’augmenter la charge en munitions à 500 cartouches par arme.

Bombes :
Jusqu\à 6 bombes d\emploi général “M64” de 500 lb
Jusqu\à 4 bombes d\emploi général “M65” de 1000 lb
Jusqu\à 2 bombes d\emploi général “M66” de 2000 lb

Roquettes:
6 fusées non guidées “M8” dans deux lanceurs “M10” qui peuvent être largués.

Longueur : 10,89 m (35,73 feet)
Envergure : 15,85 m (52 feet)
Surface alaire : 30,4 m² (327 feet²)

Premier engagement : 1944

Caractéristiques

• In addition to the automatic single-stage supercharger, each engine is equipped with the automatic turbo-supercharger.
• The turbo-supercharger is powered by the engine exhaust backpressure and is regulated automatically by the pilot throttle control in the cockpit using the shutters on the exhaust pipes.
• It should be noted that turbocharger RPM changes relatively slowly and not immediately after a control lever adjustment. For instance, during takeoff its necessary to keep the brakes pressed for several seconds after moving the throttle to takeoff position and begin the run only when the turbocharger RPM increases sufficiently to reach 54 inches of pressure.
• The automatic fuel mixture control maintains optimal mixture if mixture lever is set to Auto Rich (70%) position. To use automatic mixture leaning to reduce the fuel consumption during flight set the mixture lever to Auto Lean (30%) position. In a case of malfunction of the automatic mixture control, the mixture lever should be set to Full Rich (move the lever completely forward) position. To stop the engine, set it to the Idle Cut Off (0%) position.
• The automatic engine governor keeps the set engine RPM by adjusting the propeller pitch using an electric actuator (it is possible to turn it off and control the propeller pitch manually). The propellers can be feathered.
• To check a low fuel level warning lamps, press and hold the corresponding button (RShift+I by default).
• The aircraft has pitch and yaw flight-control trimmers.
• Landing flaps have a hydraulic actuator and can be extended to any angle up to 40°. There is also a fixed “maneuver” flaps position that can be set by a short flaps button press (“F” by default).
• The aircraft is equipped with hydraulic aileron actuators, making their operation and good roll performance at high speeds possible. The actuators are turned on using a special valve on the left side of the cockpit and require at least 1200 psi pressure in the hydraulic system, so they should be turned off if there is only one engine running. In the sim, they are turned on and off automatically.
• The aircraft has independent left and right hydraulic wheel brake controls. To apply either brake push the upper part of the rudder pedal.
• The aircraft is equipped with a parking brake system.
• The landing gear indicator lamp lights up if the landing gear is neither extended nor retracted. The extension of the nose wheel can also be checked by its reflection in the mirrors on the inner sides of the engine nacelles and by the pressure drop in the hydraulic system during the landing gear operation.
• There are signal lamps warning about the low fuel level in the outer wing tanks (the primary fuel source) and separate fuel indicators for the left and right fuel tank pairs.
• The canopy has an emergency release system for bailouts.
• The windows on the sides of the canopy can be lowered during flight, but this can cause the excessive shaking of the plane.
• The electric bomb controller allows dropping the bombs one by one from the left and right racks or by pairs.
• The unguided rockets are launched using the electric controller which allows single, pair, triple and salvo (all rockets at 0.1 seconds interval) launch. The rocket containers are jettisonable.

Basic data and recommended positions of the aircraft controls:

1. Starting the engine:
   • recommended position of the mixture control lever: Auto Rich (auto mixture control)
   • recommended position of the oil radiator / cowl flaps flap control handle: auto radiator control
   • recommended position of the prop pitch control handle: 0%
   • recommended position of the throttle lever: 20%
   • before taxiing, the parking brake must be released

2. Recommended mixture control lever positions for various flight modes: Auto Rich (auto mixture control)

3. Recommended positions of the oil radiator / cowl flaps flap control handle for various flight modes: auto control of oil radiators / cowl flaps

4. Approximate fuel consumption at 2000 m altitude:
   • Cruise engine mode: 15.2 l/min
   • Combat engine mode: 24.1 l/min

Modifications



Munitions supplémentaires

Munitions supplémentaires pour les mitrailleuses: 500 pour chacune mitrailleuses.

Masse supplémentaire : 99.3 kg (218.9 lbs)
Perte estimée de vitesse : 0 km/h 

Additional bomb racks

Underwing bomb holders

6*500 lb General Purpose Bomb M64:

Additional mass: 1568 kg (3457 lbs)
Ammunition mass: 1524 kg (3360 lbs)
Rack mass: 44 kg (97 lbs)
Estimated speed loss before drop: 52 km/h (32.3 mph)
Estimated speed loss after drop: 19 km/h (12.0 mph)

4*1000 lb General Purpose Bomb M65:

Additional mass: 2092 kg (4612 lbs)
Ammunition mass: 2048 kg (4515 lbs)
Rack mass: 44 kg (97 lbs)
Estimated speed loss before drop: 60 km/h (37.0 mph)
Estimated speed loss after drop: 19 km/h (12.0 mph)


General purpose bombs

General purpose bombs (underwing)

2*500 lb General Purpose Bomb M64:

Additional mass: 508 kg (1120 lbs)
Estimated speed loss before drop: 9 km/h (5.5 mph)
Estimated speed loss after drop: 2 km/h (1.2 mph)

2*1000 lb General Purpose Bomb M65:

Additional mass: 1024 kg (2324 lbs)
Estimated speed loss before drop: 19 km/h (11.6 mph)
Estimated speed loss after drop: 2 km/h (1.2 mph)

2*2000 lb General Purpose Bomb M66:

Additional mass: 1858 kg (4096 lbs)
Estimated speed loss before drop: 23 km/h (14.2 mph)
Estimated speed loss after drop: 2 km/h (1.2 mph)


Bendix MN-26

Goniometre pour la radionavigation
Masse supplementaire : 17,5 kg (38.6 lbs)
Perte estimee de vitesse : 1 km/h 

M8 rockets

Six M8 rockets in jettisonable M10 launchers

Additional mass: 171.9 kg (379 lbs)
Ammunition mass: 115.9 kg (256 lbs)
Racks mass: 56 kg (123 lbs)
Estimated speed loss before launch: 18 km/h (11.4 mph)
Estimated speed loss after launch: 13 km/h (8.2 mph)
Estimated speed loss after drop: 4 km/h (2.5 mph)