一体化内转式乘波前体进气道研究

Up to now, the streamline tracing inward turning inlet design strudy has two short comings. The first one is in the designing process, the basic flow field for the inward turning inlet has too many times shock wave reflections and the exit flow characteristics are not uniform and even the inner compression ratio can not be adjusted easily because the basic flow filed's compression surface constrain. Form the other point of view, for the integration design of the inward turning inlet with vehicle's forebody is a big difficulty. The presennt design methods is mainly depending on geommetry modification. This method has obviously disadvantages. It destroy the original inlet's flow characteristics and can not in herit the basic flow field's high performance. This method is depended on artificial experience and do not according with aerodynamic principles. Present project will put forward and fulfil the study on shock cancel and flow field controllable stream line tracing inward turning cone design methods. Present project will study in three aspects: The first one is studing the design methods for exit flow field uniformity, inner compression ratio controllable and sencond reflect shock cancel inward turning cone. The second aspect is studing shock cancel flow field controllable stream line tracing inward turning cone design methods and performance comparison with truncated Busemann and nozlle stream line tracing inlet. The third aspect is studying the integrated inward turning inlet-forebody design methods and its performance analysis.The forth aspect is the experimental study on exit flow field uniformity and controllable, shock cancel stream line tracing inward turning inlet.

当前流线追踪内转式进气道研究在自身的设计技术及前体/进气道一体化技术方面都存在不足。在内转式进气道自身设计技术方面，基准流场中存在多次激波反射、出口参数不均匀、进气道内收缩比受基准流场型面限制不易调节。 在内转式进气道和前体的一体化方面，主要采用几何修型技术，修型进气道对原始进气道的性能改变较为明显，不能完全继承高性能基准流场的特性，且几何修型存在人为经验的制约，不完全符合气动原理。 本项目开展一体化内转式乘波前体进气道技术研究，在四个方面开展工作:1.出口参数均匀可控、内收缩比可调可控的新型消波基准流场设计研究；2.可控消波流线追踪内转式进气道的设计及性能分析研究；3.基于流线渐变、流场控制及密切内锥轴对称技术的一体化内转式乘波前体进气道设计分析研究 4.一体化内转式乘波前体进气道风洞实验研究。

当前流线追踪内转式进气道研究在自身的设计技术及前体/进气道一体化技术方面都存在不足。在内转式进气道自身设计技术方面，基准流场中存在多次激波反射、出口参数不均匀、进气道内收缩比受基准流场型面限制不易调节。 在内转式进气道和前体的一体化方面，主要采用几何修型技术，修型进气道对原始进气道的性能改变较为明显，不能完全继承高性能基准流场的特性，且几何修型存在人为经验的制约，不完全符合气动原理。本项目开展一体化内转式乘波前体进气道技术研究，在四个方面开展工作:1.出口参数均匀可控、内收缩比可调可控的新型消波基准流场设计研究；2.可控消波流线追踪内转式进气道的设计及性能分析研究；3.基于流线渐变、流场控制及密切内锥轴对称技术的一体化内转式乘波前体进气道设计分析研究 4.一体化内转式乘波前体进气道风洞实验研究。在上述工作基础上，最终建立了一体化内转式乘波前体进气道的设计方法；获得的构型兼顾了内锥乘波特性和三维压缩特性；其性能得到了试验验证。