Fiche technique:
Indicated stall speed in flight configuration: 175..212 km/h (109..131 mph)
Indicated stall speed in takeoff/landing configuration: 143..174 km/h (89..108 mph)
Dive speed limit: 805 km/h (500 mph)
Maximum load factor: 11.0 G
Stall angle of attack in flight configuration: 16.2 °
Stall angle of attack in landing configuration: 15.4 °
Maximum true air speed at sea level, engine mode - WEP: 575 km/h (357 mph)
Maximum true air speed at 7000 m (22960 feet), engine mode - WEP: 727 km/h (451 mph)
Maximum true air speed at sea level, engine mode - Combat: 518 km/h (322 mph)
Maximum true air speed at 9000 m (29530 feet), engine mode - Combat: 685 km/h (426 mph)
Maximum true air speed at sea level, engine mode - Cruise: 485 km/h (301 mph)
Maximum true air speed at 10000 m (32800 feet), engine mode - Cruise: 651 km/h (404 mph)
Service ceiling: 11580 m (38000 feet)
Climb at engine mode - WEP
Climb rate at sea level: 18.5 m/s (3642 feet/min)
Climb rate at 3000 m (9843 feet): 18.1 m/s (3559 feet/min)
Climb rate at 6000 m (19685 feet): 16.9 m/s (3338 feet/min)
Climb at engine mode - Combat
Climb rate at sea level: 12.6 m/s (2480 feet/min)
Climb rate at 3000 m (9843 feet): 11.9 m/s (2342 feet/min)
Climb rate at 6000 m (19685 feet): 10.7 m/s (2106 feet/min)
Maximum performance turn at sea level: 27.0 s, at 322 km/h (200 mph) IAS.
Maximum performance turn at 3000 m (9843 feet): 30.0 s, at 330 km/h (205 mph) IAS.
Flight endurance at 3000 m (9843 feet): 2 h, at 370 km/h (230 mph) IAS.
Takeoff speed: 177..210 km/h (110..130 mph)
Glideslope speed: 179..220 km/h (111..135 mph)
Landing speed: 175..205 km/h (110..127 mph)
Landing angle: 11.9 °
Note 1: the data provided is for international standard atmosphere (ISA).
Note 2: flight performance ranges are given for possible aircraft mass ranges.
Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass and 50%25 of fuel.
Note 4: turn times are given for WEP power.
Engine:
Model: R-2800-59
Maximum power in WEP mode at sea level: 2600 HP
Maximum power in Combat mode at sea level: 1950 HP
Maximum power in Cruise mode at sea level: 1620 HP
Maximum power in WEP mode at 7000 m (22970 feet): 2600 HP
Maximum power in Combat mode at 9000 m (29530 feet): 1900 HP
Maximum power in Cruise mode at 10500 m (34450 feet): 1600 HP
Engine modes:
Cruise (unlimited time): 2550 RPM, 42.0 inch Hg
Combat power (up to 15 minutes): 2700 RPM, 52.0 inch Hg
WEP (up to 5 minutes): 2700 RPM, 64.0 inch Hg
Maximum continuous turbocharger RPM: 20000
Maximum turbocharger RPM for up to 15 minutes: 22000
Oil rated temperature in engine intake: 60..95 °C
Oil maximum temperature in engine intake: 100 °C
Supercharger gear shift altitude: single gear
Empty weight: 4665 kg (10285 lb)
Minimum weight (no ammo, 10%25 fuel, 4 MG removed): 5033 kg (11096 lb)
Standard weight: 6213 kg (13697 lb)
Maximum takeoff weight: 7867 kg (17343 lb)
Fuel load: 829 kg (2551 lb) / 1155 l (305 gal)
Useful load: 3202 kg (7058 lb)
Forward-firing armament:
8 x 12.7mm machine gun "M2.50", 267 rounds, 850 rounds per minute, wing-mounted
It is possible to remove 2 or 4 machine guns and/or increase the ammo load to 425 rounds per gun.
Bombs:
Up to three 500 lb general purpose bomb "M64"
Up to two 1000 lb general purpose bomb "M65"
Rockets:
6 x unguided rockets "M8" in two "M10" launchers that can be jettisoned
Length: 11.00 m (36.09 feet)
Wingspan: 12.43 m (40.78 feet)
Wing surface: 27.87 m² (300 feet²)
Combat debut: 1944
Additional airplane configurations list:
150 grade fuel
150 grade fuel, which allows increased manifold pressure up to 70 inches.
Additional ammo for machine guns: 425 for each gun.
8 machineguns:
Additional mass: 178.2 kg (393 lbs)
Estimated speed loss: 1 km/h
6 machineguns:
Additional mass: 133.6 kg (294.8 lbs)
Estimated speed loss: 0 km/h
4 machineguns:
Additional mass: 89.1 kg (196.5 lbs)
Estimated speed loss: 0 km/h
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)
Removal of 4 external wing-mounted machine guns to reduce total weight
Removed mass: 280.6 kg (618.7 lbs)
Removed ammunition mass: 150.6 kg (332.1 lbs)
Removed guns mass: 130 kg (286.6 lbs)
Estimated speed gain: 6 km/h (3.7 mph)
Removal of 2 external wing-mounted machine guns to reduce total weight
Removed mass: 140.3 kg (309.3 lbs)
Removed ammunition mass: 75.3 kg (166.0 lbs)
Removed guns mass: 65 kg (143.3 lbs)
Estimated speed gain: 3 km/h (1.8 mph)
Fixed loop radio compass for navigation with radio beacons
Additional mass: 17,5 kg (38.6 lbs)
Estimated speed loss: 1 km/h
Operation features:
- 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%25).
- 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%25) position. To use automatic mixture leaning to reduce fuel consumption during flight it is necessary to set the mixture lever to Auto Lean (60%25) position. In the case of malfunction of the automatic mixture control the mixture lever should be set to Full Rich (100%25) position. To stop the engine mixture lever should be set to the Cut Off (0%25) 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.
Technique de bombardement:
Technique d'utilisation des roquettes:
Bonjour à tous. J'ai une petite question. A quoi sert cette manette prés de la manette des gaz (Water , Sol) ?
Merci d'avance.
