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一、引言美国海军F/A—18A“大黄蜂”战斗机是麦克唐纳·道格拉斯公司与诺斯罗普公司联合研制的,装有两台通用电气公司研制的F404—GE—400型发动机。由于F/A—18A要有非常高的机动能力,因此要求其进气道/发动机系统在最大迎角和侧滑角时要很好地相容。飞机在做极端机动飞行时可能在发动机迎风面引起很大的进气道动态畸变,这种畸变尽管只有几毫秒,但也会严重地影响发动机的稳定性。为了研究和估算这种进气道/发动机的相容性,对F/A—18A 整个战斗机动范围内的所有亚音速与超音速临界机动条件都做了
I. INTRODUCTION The U.S. Navy F / A-18A “Hornet” fighter was jointly developed by McDonnell Douglas and Northrop Corporation and equipped with two F404-GE-400 engines developed by General Electric Company. Due to the very high maneuverability of the F / A-18A, its intake / engine system is required to be well compatible at maximum angle of attack and side slip angle. Aircraft in extreme maneuvers may cause significant air inlets on the windward side of the engine, a distortion that, although only a few milliseconds, can seriously affect engine stability. In order to study and evaluate this port / engine compatibility, all subsonic and supersonic critical maneuver conditions throughout the F / A-18A maneuvering range were done