进口流场与发动机工作稳定性试飞
FLIGHT TESTS FOR AIR INTAKE FLOWFIELD AND ENGINE OPERATING STABILITY
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摘要: 某超音速飞机,在一定的高度和速度范围内,通过“全加力”加速平飞,平飞时发动机加速与节流、跃升和等Ma数爬升等试飞。以调节中心锥体上6个测压点的压力变化规律为依据,进气道出口“十”字形测压耙(图1)的压力分散度值定性地描述流场变化的趋势.来评定进气道与发动机匹配相容性。试飞结果表明:进气道以较弱的超临界状态与发动机相匹配工作;但时,进气道以较严重的超临界状态与发动机相匹配,显得喉道面积偏小;此外大攻角跃升和高空小表速接通加力时,各发生一次空中停车。Abstract: The operating compatibility between air intake and engine during the flighttests of a supersonic fighter is considered. The flight tests were completed under conditions of huri zontal accelerating flight, uprated and retarded throttles of the engine during horizontal flight and constant-Mach climbing with maximum and augmented thrust rating. The flow conditions at the intake and the tendency of flowfield variation at the inlet of the engine were evaluated by means of six prossure tappings at the variable intake cone and a cross rake pressure probe at the exit of the intake. The technical measures have been taken to cope with the engine troubles and their effects are also described in the paper.
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