il2_specs

P-47D-22

Description

Vitesse de décrochage indiquée en configuration de vol : 175..212 km/h (109..131 mph)
Vitesse de décrochage indiquée en configuration de décollage/atterrissage : 143..174 km/h (89..108 mph)

Vitesse limite de piqué : 805 km/h (500 mph)
Facteur de charge maximum : 11.0 g
Angle d\attaque de décrochage en configuration de vol : 16.2 °
Angle d\attaque de décrochage indiquée en configuration d\atterrissage : 15.4 °

Vitesse sol au niveau de la mer, régime moteur - Urgence: 575 km/h (357 mph)
Vitesse sol maximale à 7000 m (22960 feet), régime moteur - Urgence: 727 km/h (451 mph)

Vitesse sol au niveau de la mer, régime moteur - Combat: 518 km/h (322 mph)
Vitesse sol maximale à 9000 m (29530 feet), régime moteur - Combat: 685 km/h (426 mph)

Vitesse sol au niveau de la mer, régime moteur - Continu: 485 km/h (301 mph)
Vitesse sol maximale à 10000 m (32800 feet), régime moteur - Continu: 651 km/h (404 mph)

Plafond opérationnel : 11580 m (38000 feet)

Régime moteur - Urgence
Taux de montée au niveau de la mer: 18.5 m/s (3642 feet/min)
Taux de montée à 3000 m (9843 feet): 18.1 m/s (3559 feet/min)
Taux de montée à 6000 m (19685 feet): 16.9 m/s (3338 feet/min)

Régime moteur - Combat
Taux de montée au niveau de la mer: 12.6 m/s (2480 feet/min)
Taux de montée à 3000 m (9843 feet): 11.9 m/s (2342 feet/min)
Taux de montée à 6000 m (19685 feet): 10.7 m/s (2106 feet/min)

Virage à 360° au niveau de la mer en: 27.0 s, à 322 km/h (200 mph) vitesse indiquée (IAS).
Virage à 360° à 3000 m (9843 feet): 30.0 s, à 330 km/h (205 mph) vitesse indiquée (IAS).

Endurance à 3000 m (9843 feet): 2 h, à 370 km/h (230 mph) vitesse indiquée (IAS).

Vitesse de décollage : 177..210 km/h (110..130 mph)
Vitesse d\approche : 179..220 km/h (111..135 mph)
Vitesse d\atterrissage : 175..205 km/h (110..127 mph)
Angle d\atterrissage : 11.9 °

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 50% 25 de carburant.
Note 4 : le temps de virage est à régime Urgence.

Moteur :
Modèle : R-2800-59
Puissance maximale àu régime de Urgence au niveau de la mer: 2600 cv
Puissance maximale au régime de Combat au niveau de la mer: 1950 cv
Puissance maximale au régime continu au niveau de la mer: 1620 cv

Puissance maximale au régime de Urgence à 7000 m (22970 feet): 2600 cv
Puissance maximale au régime de combat à 9000 m (29530 feet): 1900 cv
Puissance maximale au régime continu à 10500 m (34450 feet): 1600 cv

Performance du moteur :
Continu (durée illimitée) : 2550 tr/min, 42.0 inch Hg
Combat (jusqu\à 15 minutes) : 2700 tr/min, 52.0 inch Hg
Urgence (jusqu\à 5 minute) : 2700 tr/min, 64.0 inch Hg

Régime de turbocompresseur maximal en continu: 20000
Régime maximal du turbocompresseur jusquà 15 minutes: 22000

Température de fonctionnement d\huile à l\admission du moteur : 60..95 °C
Température maximale d\huile à l\admission du moteur : 100 °C

Altitude de changement d\étage du compresseur : étage simple

Masse à vide : 4665 kg (10285 lb)
Masse minimale (sans munitions, 10% de carburant, 4 MG enlevés) : 5033 kg (11096 lb)
Masse standard : 6213 kg (13697 lb)
Masse maximale au décollage : 7867 kg (17343 lb)
Masse de carburant : 829 kg (2551 lb) / 1155 l (305 gal)
Charge utile : 3202 kg (7058 lb)

Armement offensif :
8 mitrailleuse M2 de 12.7 mm, 267 coups, 850 coups par minute, dans l\aile
Il est possible de retirer 2 ou 4 mitrailleuses et / ou d’augmenter la charge en munitions à 425 cartouches par arme.

Bombes :
Jusqu\à 3 bombes d\emploi général “M64” de 500 lb
Jusqu\à 2 bombes d\emploi général “M65” de 1000 lb

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

Longueur : 11.00 m (36,09 feet)
Envergure : 12.43 m (40,78 feet)
Surface alaire : 27.87 m² (300 feet²)

Premier engagement : 1944

Caractéristiques

• In addition to the automatic single stage supercharger, the engine is equipped with a turbocharger that the pilot can control.
• The turbocharger is powered by the engine exhaust back pressure which can be set by a lever in the cockpit and maintained automatically using the throttle shutters on the exhaust pipes.
• The air compressed in the turbocharger goes to the intercooler where it is cooled by the incoming airflow. The cool compressed air goes to the carburetor and the resulting fuel-air mixture goes to the supercharger.
• The temperature of the air after the intercooler is indicated by a separate gauge. The pilot can control the intercooler flaps using the toggle switch and observe their position using the indicator on the left. Their default position is neutral (50%).
• The turbocharger RPM is controlled by the lever in the cockpit (“Left Shift” and “+”/”-“ keys by default). At the back lever position the throttle shutters are fully open and exhaust gases all go to the atmosphere, resulting in minimal turbocharger RPM. At the forward lever position, the exhaust back pressure and the resulting turbocharger RPM are at maximum. It should be noted that the RPM will change with the altitude even if the lever is kept in the same position. The turbocharger RPM is indicated by a dedicated gauge.
• The total engine power should be controlled using the joint method when the three levers - RPM lever, throttle lever and turbocharger lever are moved together. However, in certain cases (for instance, when going higher than the critical altitude) the turbocharger lever should be adjusted separately.
• It should be noted that turbocharger RPM changes relatively slowly and not immediately after the control lever adjustment.
• The aircraft is equipped with the water injection system that boosts the power in the emergency mode. When this system is engaged, the exhaust back pressure and turbocharger RPM increase automatically while the mixture becomes leaner. The water supply is good for around 7 minutes at the emergency power.
• The engine is equipped with an automatic fuel mixture control which maintains optimal mixture if the mixture lever is set to Auto Rich (85%) position. To use automatic mixture leaning to reduce fuel consumption during flight it is necessary to set the mixture lever to Auto Lean (60%) position. In the case of malfunction of the automatic mixture control the mixture lever should be set to Full Rich (100%) position. To stop the engine mixture lever should be set to the Cut Off (0%) position.
• Engine RPM has an automatic governor and it is maintained at the required RPM corresponding to the governor control lever position. The governor automatically controls the propeller pitch to maintain the required RPM.
• Oil radiators shutters are manually operated.
• The aircraft has trimmers for all flight-controls: pitch, roll and yaw.
• Landing flaps have a hydraulic actuator and they can be extended to any angle up to 40°.
• It is forbidden to open the cowl flaps at speeds exceeding 225 mph, perform sharp maneuvers with the opened cowl shutters and dive with the opened intercooler shutters.
• The aircraft has a manual control for the tailwheel lock. The tailwheel should be locked when taxiing straight for a long distance and before takeoff and landing.
• 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 signal lamp lights up when the landing gear is up and the throttle is in the backward position or when the landing gear is down, but the throttle is in the forward position.
• It should be noted that the aircraft requires a long takeoff run - around 650 meters at standard load and 1500 meters at maximum takeoff weight. It is possible to lower the flaps to 10-20 degrees to shorten the takeoff run. 
• The aircraft is equipped with one fuel gauge, but two indicator needles for the forward and rear fuel tanks.
• The engine consumes much fuel at the combat power mode - around 4.5 gallons per minute.
• The canopy has an emergency release system for bailouts.
• The aircraft is equipped with the manual bomb release system for each of the three bomb racks.
• The unguided rockets are launched using the electric controller which allows single, pair, triple and salvo (all rockets at 0.1 seconds interval) launch.
• There is a backup mechanical sight which can be used if the main sight is damaged.

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 radiator/cowl flap control handle: open 50%
   • recommended position of the prop pitch control handle: 100%
   • recommended position of the throttle lever: 10%
   • before taxiing, you must unlock the tailwheel
   • before taxiing, the parking brake must be released
2. Recommended mixture control lever positions for various flight modes: Auto Rich (auto mixture control)

3.1 Recommended positions of cowl flaps for various flight modes:
- takeoff: open 50%
- climb: open 100%
- cruise flight: close
- combat: open 50%

3.2 Recommended positions of the oil radiator control handle for various flight modes:
- takeoff: open 50%
- climb: open 100%
- cruise flight: close
- combat: open 50%

1. Approximate fuel consumption at 2000 m altitude:
   • Cruise engine mode: 14.3 l/min
   • Combat engine mode: 15.7 l/min

Modifications



150 grade fuel

150 grade fuel, which allows increase manifold pressure up to 70 inch.


Munitions supplémentaires

Munitions supplémentaires pour les mitrailleuses: 425 pour chacune mitrailleuses.

8 mitrailleuses:
Masse supplémentaire : 178.2 kg (393 lbs)
Perte estimée de vitesse : 1 km/h

6 mitrailleuses:
Masse supplémentaire : 133.6 kg (294.8 lbs)
Perte estimée de vitesse : 0 km/h

4 mitrailleuses:
Masse supplémentaire : 89.1 kg (196.5 lbs)
Perte estimée de vitesse : 0 km/h 

Ground attack modification

Underwing and underbelly racks for bombs and rockets

Racks only:

Rack mass: 30 kg (66.2 lbs)
Estimated speed loss: 7 km/h (4.4 mph)

3*500 lb General Purpose Bomb M64:

Additional mass: 792 kg (1746.4 lbs)
Ammunition mass: 762 kg (1680.2 lbs)
Rack mass: 30 kg (66.2 lbs)
Estimated speed loss before drop: 35 km/h (21.8 mph)
Estimated speed loss after drop: 12 km/h (7.5 mph)

2*1000 lb General Purpose Bomb M65:

Additional mass: 1054 kg (2324.1 lbs)
Ammunition mass: 1024 kg (2257.9 lbs)
Rack mass: 30 kg (66.2 lbs)
Estimated speed loss before drop: 47 km/h (29.2 mph)
Estimated speed loss after drop: 10 km/h (6.2 mph)

6*M8 rockets in M10 jettisonable launchers:

Additional mass: 179.9 kg (396.7 lbs)
Ammunition mass: 115.9 kg (255.6 lbs)
Racks mass: 64 kg (141.1 lbs)
Estimated speed loss before launch: 27 km/h (16.8 mph)
Estimated speed loss after launch: 21 km/h (13.1 mph)
Estimated speed loss after drop: 8 km/h (5.0 mph)


4 mitrailleuses M2 .50

Retrait des 4 mitrailleuses externes sur les 6 pour réduire la masse totale
Masse enlevée : 280.6 kg (618.7 lbs)
Masse des munitions enlevées : 150.6 kg (332.1 lbs)
Masse des mitrailleuses enlevées : 130 kg (286.6 lbs)
Gain estimé de vitesse : 6 km/h (3.7 mph) 

6 mitrailleuses M2 .50

Retrait des 2 mitrailleuses externes sur les 6 pour réduire la masse totale
Masse enlevée : 140.3 kg (309.3 lbs)
Masse des munitions enlevées : 75.3 kg (166.0 lbs)
Masse des mitrailleuses enlevées : 65 kg (143.3 lbs)
Gain estimé de vitesse : 3 km/h (1.8 mph) 

Bendix MN-26

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