发动机喷流与飞机机体绕流存在相互干扰，但飞机绕流状态下排气系统推力特性试验研究不足，原因是传统喷流试验平台仅模拟排气系统工作状态对应的落压比条件而不能模拟飞机前方来流条件。超声速飞机飞行速域较宽，覆盖低速、亚声速、跨声速与超声速等多个速域，导致发动机喷流与飞机机体绕流相互干扰作用更加复杂多变。超声速引射排气系统推力特性风洞试验研究提出了超声速飞机机体约束下引射排气系统推力特性风洞试验方法，获取了超声速飞机多个飞行速域绕流状态下引射排气系统推力特性变化规律。试验研究表明：在不同速域内，飞机绕流状态下超声速引射排气系统设计状态和非设计状态推力特性差异较大，设计状态推力系数可达到0.98以上，非设计状态推力系数最低降至0.79附近，试验研究结果可为超声速引射排气系统设计点和非设计点性能权衡设计提供重要依据。在此基础上，基于数值模拟结果对超声速引射排气系统设计状态和非设计状态的流场特征及其与推力特性的关系进行了分析。
There is mutual interference between engine jet and airframe flow, but there is not enough research on thrust characteristic of exhaust system under the condition of airframe flow. The reason is that the traditional jet test platform only simulates the nozzle pressure ratio condition corresponding to the working condition of the exhaust system, but it can't simulate the flow condition in front of the aircraft. The flight velocity domain of supersonic aircraft is wide, covering many speed domains such as low speed, subsonic speed, transonic speed and supersonic speed, which make the interaction between engine jet and airframe flow more complex and changeable. This paper presents a wind tunnel test method for the thrust characteristics of supersonic ejector exhaust system under the constraints of supersonic aircraft airframe, and obtains the variation law of the thrust characteristics of the ejector exhaust system under the conditions of multi-flight velocity domain circumfluence of supersonic aircraft. The experimental results show that there is a great difference between the design state and the non-design state thrust characteristics of the supersonic ejector exhaust system in different speed range. The thrust coefficient of the design state can reach above 0.98 and the minimum thrust coefficient of the non-design state can be reduced to around 0.80. The experimental results can provide an important basis for the design of the supersonic ejector exhaust system and the performance tradeoff design of the non-design point. Based on the results of numerical simulation, the characteristics of the flow field and the relationship between the design state and the non-design state of the supersonic ejector exhaust system and the thrust characteristics are analyzed.
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