DCS: F-86F "佩刀"

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北美F-86F "佩刀" 是1950年代中期最得力的战斗机。这种后掠翼单发喷气机是西方在朝鲜战争中最重要的飞机,它经常与俄制MiG-15纠缠。这场艰苦的战斗不仅存在于朝鲜的天空,也是两个优秀的东方和西方的飞机制造商之间的战斗。除了其主要作用作为空中战斗机,佩刀也会携带炸弹和空对地火箭来攻击地面目标。

Belsimtek的"佩刀"是目前为止这架战鹰最真实的模拟飞行游戏。感受驾驶"佩刀" - 专业水平的飞行模型、交互式的驾驶舱、功能齐全的武器、详细的损伤模型和丰富的细节。体验"佩刀"在战斗种的优势和劣势,找出老练的战斗机飞行员经常回味"佩刀"作为他们最享受的飞机的原因。

作为DCS世界的一部分, F-86F佩刀完全体现了作战环境,武器系统和空地的作战能力。

发行: 2016-04-01

Performance characteristics

Normal crew: 1

Maximum allowable gross: 20,611 lbs / 9,348 kg

Basic weight: 11,125 lbs / 5,046 kg

Useful load (with pilot 230 lbs): 6,607 lbs / 2,996 kg

Weight with payload for normal mission: 15,175 lbs / 6,883 kg

Fuel usable capacity internal (JP-4, 0.778 kg/l): 2,826 lbs / 435 gal / 1,282 kg / 1,647 l

Fuel consumption rate (for loiter at 30,000 ft, CAS 192 kts, RPM 74%, gross weight 12,296-15,138 lbs): ~1,150 lbs/h / 522 kg/h

Normal cruise speed (for maximum range at 35,000 ft, RPM 78%, gross weight 12,296-15,138 lbs): 260 kts / 482 km/h

Maximum speed at sea level: 600 kts / 1,111 km/h

Maximum speed at 33,000 feet: 313 kts / 580 km/h

Service ceiling (for weight 14,000 lbs): 52,000 ft / 15,850 m

Maximum rate of climb: 9,500 ft/min / 2,835 m/min

Maximum range: 1,395 nm / 2,584 km

Armament

F-86F Sabre can perform different combat roles that include destruction of both air and ground targets. Integral weapons and various pod-type armament make it possible to show its combat capabilities:

- 6 Colt-Browning М3 machine guns (calibre – 12.7 mm, rate of fire – 1100 rounds per minute, weapons capacity – 300 rounds per machine gun)

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- 2 AN-M64 bombs

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- 16 HVAR unguided rockets

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General layout

F-86F general layout
  1. Command radio antenna
  2. J47-GE-27 engine
  3. Aft radio compartment
  4. Directional indicator transmitter
  5. Radio compass sense antenna
  6. Radio compass loop antenna
  7. Ejection seat
  8. Rear-vision mirror
  9. Gun-bomb-rocket sight
  10. Radar ranging equipment
  1. Battery
  2. Radar antenna
  3. Gun camera
  4. Retractable landing and taxi light
  5. Retractable landing light
  6. Oxygen cylinders
  7. Guns barrels
  8. Kick step
  9. Ammunition compartment
  10. Ammunition compartment access door
  1. Gun compartment
  2. Forward fuselage tank (lower cell)
  3. Forward fuselage tank (upper cell)
  4. Identification radar antenna
  5. Outer wing fuel tank
  6. Pitot head
  7. Aft fuselage fuel tank
  8. Speed brake
  9. Controllable horizontal tail (elevator and controllable stabilizer)
  10. Fin

Engine

The J47-GE-27 jet turbine engine installed on the F-86F was manufactured by General Electric and has a static thrust of about 6,000 pounds (2,680kgf).

J47-GE-27 jet turbine engine
  1. Air Intake
  2. Accessory Section
  3. Compressor Section
  4. Fuel Nozzle
  1. Combustion chamber
  2. Crossover Ignition Tube
  3. Turbine
  4. Exhaust Cone

The jet turbine model is based on the simulation of the gas-dynamic duct, the condition of which is closely interrelated to the air intake, compressor, combustion chamber, turbine, and exhaust cone models of operation. In addition to this, the engine fuel control system is fully simulated. All these models interrelate with each other and this makes it possible to attain manifestation of the following features:

  • The successful start of the engine is provided only if the startup operation has been performed correctly: otherwise hung start and dead-start are possible
  • Idle RPM depends on the flight mode: based on altitude and Mach number as well as on the atmospheric conditions of pressure and temperature
  • Short engine over-speed and overheat may occur at active throttle input
  • Acceleration time and throttle retardation as well as engine controllability (reaction lag on throttle) depend on RPM
  • Value of the jet pipe temperature is modeled in exact detail and it depends on the engine operating condition, flight mode and atmospheric conditions
  • Specific fuel consumption nonlinearly depends on the engine operating condition and flight mode
  • Dynamics of the engine operating conditions (RPM and gas temperature) are simulated correctly during engine start up, in flight, and during engine shutdown
  • The compressor autorotation regime of the engine from the approach flow was implemented as well as the ability to perform an air start (the success of which depends on the autorotation RPM)
  • Penetration into regimes of uneven engine operation such as stall, flameout in the combustion chamber, etc. may occur
  • Engine running at zero-G and negative-G load factors is restricted by capabilities of the fuel-feed system
Idle RPM

Engine fuel control system

Fuel consumption to the engine is governed by the fuel management system (engine fuel control system) consisting of the main fuel control system and emergency (back-up) fuel control system. The emergency system is used to maintain the fuel flow to the engine in case of a failure of the main system.

Engine fuel control system
A. Main fuel flow
B. Emergency fuel flow
C. Main by-pass flow
D. Emergency by-pass flow
E. Electrical connection
F. Mechanical linkage
G. Check valve
  1. From fuel supply
  2. Shutoff valve
  3. Fuel filter
  4. Engine waster switch
  5. Dual fuel pump
  6. Emergency fuel switch
  7. Emergency fuel regulatorc
  8. Fuel filter
  1. Main fuel regulator
  2. Throttle
  3. Stopcock
  4. Fuel flow meter
  5. Small-slot manifold (starting and operating)
  6. Flow divider
  7. Large-slot manifold (operating)
  8. Fuel nozzle