高超声速二元进气道顶板移动变几何方案数值模拟

流体力学与飞行力学

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高超声速二元进气道顶板移动变几何方案数值模拟

张林, 张堃元, 金志光, 南向军, 王磊

南京航空航天大学能源与动力学院, 江苏南京 210016

收稿日期:2011-10-26 修回日期:2011-11-25 出版日期:2012-10-25 发布日期:2012-10-25
通讯作者: 张堃元 E-mail:zkype@nuaa.edu.cn
基金资助:
国家自然科学基金(90916029)

Numerical Simulation of a Variable Geometry Hypersonic 2D Inlet Designed with Compressible Ramp Movable

ZHANG Lin, ZHANG Kunyuan, JIN Zhiguang, NAN Xiangjun, WANG Lei

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

Received:2011-10-26 Revised:2011-11-25 Online:2012-10-25 Published:2012-10-25
Supported by:
National Natural Science Foundation of China (90916029)

摘要/Abstract

摘要： 针对一种工作于马赫数Ma=4~6范围内的高超声速二元进气道,探索了一种进气道部分压缩顶板可移动的简单变几何方案,利用数值模拟研究了接力点变几何进气道的自起动性能和Ma=4~6的调节方法。结果表明:部分压缩顶板可移动简单变几何进气道方案在Ma=3.7能够实现自起动;变几何所形成的自适应放气槽放气量很小,最大放气量在2%以内,关闭自适应放气槽接力点Ma=4流量系数达到0.77;在整个工作范围内流量系数较高、总体性能较优,该变几何方案的调节方法是切实可用的。

关键词: 高超声速进气道, 变几何进气道, 部分压缩顶板移动, 起动性能, 数值模拟

Abstract: This paper investigates a variable geometry design with partially compressible ramp movable to simulate a hypersonic two-dimensional (2D) inlet working from Mach number Ma=4-6.The inlet self-starting performance at Ma=4 and the adjusting method from Ma=4 to Ma=6 are studied by means of numerical simulation. The results show that the variable geometry inlet self-start can be realized at Ma=3.7, and the discharge capacity of the adaptive bleed slot formed by the variable geometry is below 2%. When the adaptive bleed slot is closed after starting, the mass flow rate reaches 0.77 at Ma=4. This design enables the inlet to possess a high mass flow rate and good performance during the whole working range, and the adjusting method is practical and feasible.

Key words: hypersonic inlet, variable geometry inlet, partial compression ramp movable, starting characteristic, numerical simulation

中图分类号:

V231.3

张林, 张堃元, 金志光, 南向军, 王磊. 高超声速二元进气道顶板移动变几何方案数值模拟[J]. 航空学报, 2012, 33(10): 1800-1808.

ZHANG Lin, ZHANG Kunyuan, JIN Zhiguang, NAN Xiangjun, WANG Lei. Numerical Simulation of a Variable Geometry Hypersonic 2D Inlet Designed with Compressible Ramp Movable[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2012, 33(10): 1800-1808.

参考文献

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E-mail：hkxb@buaa.edu.cn

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

高超声速二元进气道顶板移动变几何方案数值模拟

Numerical Simulation of a Variable Geometry Hypersonic 2D Inlet Designed with Compressible Ramp Movable

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