| 摘要: |
| 根据激波和膨胀波理论,设计了Ma=5.3等压力梯度曲面压缩系统。在Ma=3.85和Ma=5.3的小高超风洞完成均匀来流试验,并利用风洞壁面自然发展的附面层进行非均匀来流等压力梯度曲面压缩系统性能试验。试验发现:均匀来流下,试验模型壁面压力均按照等压力梯度规律分布,但来流马赫数Ma=5.3时出口流场均匀性较差；非均匀来流下,大量的附面层吸入不仅影响壁面压力不再呈等压力梯度分布,而且对出口流场均匀性影响也极大。 |
| 关键词: 超声速进气道 曲面压缩 等压力梯度 弯曲激波 风洞试验 |
| DOI： |
| 分类号: |
| 基金项目:自然科学基金重大研究计划(90916029)。 |
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| Experimental Investigation of Constant Pressure Gradient Curved Compression System in Non-Uniform Inflow |
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PAN Jin1,JIN Feng2,ZHANG Kun-yuan2
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(1. College of Jincheng, Nanjing University of Aeronautics and Astronautics, Nanjing 211156, China;2.College of Energy and Power, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China)
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| Abstract: |
| According to the shock wave and expansion wave theory, a model with constant pressure gradient curved compression system was designed at Ma=5.3. The curved compression model was tested in Ma=3.85and Ma=5.3wind tunnel at the condition of uniform inflow and simulated forebody boundary layer non-uniform inflow. The experimental results indicate that the pressure distribution of model surface are of constant pressure gradient feature in uniform inflows. The uniformity of outlet flowfield is worse at inflow Mach number Ma=5.3.The incoming flow non-uniformity has a dramatic effect on the pressure distribution of model surface and the uniformity of outlet flowfield. |
| Key words: Supersonic inlets Curved compression Constant pressure gradient Curved shock Wind tunnel test |
