壁面压升可控的高超轴对称进气道优化设计

向有志; 张堃元; 王磊; 高雄

壁面压升可控的高超轴对称进气道优化设计

南京航空航天大学能源与动力学院,南京 210016

基金项目: 国家自然基金重大专项(90916029)

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出版历程
- 收稿日期: 2010-11-02
- 修回日期: 2011-03-31
- 刊出日期: 2011-10-28

Optimization design of hypersonic axisymmetric inlet with controllable law of wall pressure rise

College of Energy and Power Engineering, Nanjing University Aeronautics and Astronautics, Nanjing 210016, China

摘要

摘要: 采用有旋特征线理论,研究了沿程压升规律可控的轴对称物理壁面设计方法,基于该方法,结合替代模型多目标优化设计压缩面,基于优化结果,设计了一种高超声速轴对称进气道,对其进行了数值研究,并与常规双锥、三锥轴对称进气道进行了比较.结果表明:该进气道长度比双锥进气道缩短捕获半径的32.5%;设计点其性能介于双锥与三锥之间;起动点其流量系数比双锥和三锥分别提高8.24%和12.60%,总压恢复系数比双锥和三锥分别提高4.06%和2.50%.
- 高超声速轴对称进气道 /
- 壁面压升规律 /
- 弯曲激波 /
- 曲面压缩型面 /
- 优化设计
Abstract: The design method of axisymmetric wall boundary with a controllable law of wall pressure rise was investigated using the theory of rotational characteristics.With this design method, multi-objective optimization of the compression surface was carried out on the basis of surrogate models, and then a hypersonic axisymmetric inlet was designed using the optimal solutions.The inlet was investigated through numerical simulation, and was compared with the normal double-cone and triple-cone inlet.The results show that the length of new inlet is reduced by 32.5% of the radius than the double-cone inlet;under the design point, the performance of the new inlet lies between the double-cone and triple-cone inlet;under the start point, the flow capture ratio is improved by 8.24% and 12.60%, and the total pressure recovery is improved by 4.06% and 2.50% than the double-cone and triple-cone inlet, respectively.
- hypersonic axisymmetric inlet /
- law of wall pressure rise /
- curved shock /
- curved compression surface /
- optimization design

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参考文献(12)

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