| 摘要: |
| 为了研究不同的平面斜激波流场对流线追踪"咽"式进气道性能的影响规律,寻求性能最佳的进气道,对设计马赫数为7,具有不同三维基本流场的流线追踪"咽"式进气道进行了数值模拟。研究表明:选择8-7无粘流场(即俯仰平面内的斜激波由和自由来流呈8°夹角的斜压缩面产生;偏航平面内的斜激波由和自由来流呈7°夹角的斜压缩面产生)作为基本流场设计出的流线追踪进气道压缩性能、总压恢复性能及起动性能均能满足设计要求,并有较高的捕获流量;另外,通过对其进行附面层修正,设计状态下的各性能参数都较接近无粘设计参数,并且大幅度提高了进气道的流场均匀性。 |
| 关键词: 高超进气道 内收缩 流线追踪 附面层修正 设计参数 |
| DOI： |
| 分类号:V235.21 |
| 基金项目:国家自然科学基金资助项目(90716013;10702029) |
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| Effect of design parameters and boundary layer correction on performance of jaws inlet |
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DONG Hao, WANG Cheng-peng, CHENG Ke-ming
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Coll.of Aerospace Engineering,Nanjing Univ.of Aeronautics and Astronautics,Nanjing 210016,China
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| Abstract: |
| Numerical simulations of a series of streamline traced jaws inlets have been conducted at Mach 7 to study the influence of different shock wave flow field on inlet performance.The results show that the jaws inlet based on a flow field with 8-7 planar shock wave(the ramp in pitch plane is inclined at 8° to the free stream and in yaw plane is inclined at 7° to the free stream,yielding planar shocks) and derived with the technology of streamline traced should be choose.Because the inlet has excellent compression efficiency,total pressure recovery and staring performance while the mass capture are much higher;in addition,the inlet performance on design point closed to the parameters of inviscid design and the flow field uniformity is improved significantly with boundary layer correction. |
| Key words: Hypersonic inlet Inward turning Streamline traced Boundary layer correction Design parameters |
