高超侧压进气道溢流方案的改进与分析

推进技术 ›› 2013, Vol. 34 ›› Issue (7): 873-879.

高超侧压进气道溢流方案的改进与分析

赵一龙,范晓樯,王翼,梁剑寒,王振国

国防科技大学高超声速冲压发动机技术重点实验室,湖南长沙 410073;国防科技大学高超声速冲压发动机技术重点实验室,湖南长沙 410073;国防科技大学高超声速冲压发动机技术重点实验室,湖南长沙 410073;国防科技大学高超声速冲压发动机技术重点实验室,湖南长沙 410073;国防科技大学高超声速冲压发动机技术重点实验室,湖南长沙 410073

发布日期:2021-08-15
作者简介:赵一龙(1986—),男,博士生,研究领域为高超声速推进技术。E-mail:zhaoyilong2007@126.com
基金资助:
国家自然科学基金(10802096)。

Spillage Amelioration and Analysis of Side-Compression Hypersonic Inlet

Science and Technology on Scramjet Laboratory,National University of Defense Technology, Changsha 410073,China;Science and Technology on Scramjet Laboratory,National University of Defense Technology, Changsha 410073,China;Science and Technology on Scramjet Laboratory,National University of Defense Technology, Changsha 410073,China;Science and Technology on Scramjet Laboratory,National University of Defense Technology, Changsha 410073,China;Science and Technology on Scramjet Laboratory,National University of Defense Technology, Changsha 410073,China

Published:2021-08-15

摘要/Abstract

摘要： 为了提高高超侧压进气道的性能,通过在其侧板上方添加盖板与在底板开槽的方式对其溢流方案进行了改进。对原型与改型进气道进行了来流Ma=4～7流场的数值模拟,并对两进气道进行了Ma=4时不同攻角下的起动性能试验。结果表明,低马赫数时(Ma=4,5),在总压恢复系数基本保持不变的前提下,改型进气道的流量系数较原型进气道获得大幅提升,Ma=4时,提高20.6%,Ma=5时,提高11.5%。在流量系数增加的同时,起动性能也获得大幅提升,来流为Ma=4时,由-2°攻角下起动提升为+4°攻角下依然可以实现起动。由于溢流方案的改进针对低马赫数时的进气道流场,在高马赫数时(Ma=6,7),进气道的性能基本不变。研究表明,抑制侧板间溢流的同时引入底板溢流的方式是提高高超侧压进气道综合性能的有效途径。 

关键词: 高超侧压进气道;溢流;数值模拟;风洞实验 

Abstract: In order to improve the performance of the side-compression hypersonic inlet, the spillage of such an inlet was ameliorated by adding cowls upon the sidewalls and notching on the down wall. Numerical simulation of the flow fields of the prototype inlet and the ameliorated inlet at Ma=4~7was conducted, and the starting characteristics of the two inlets at different attack angles were tested in the wind tunnel at Ma=4. The results show that the mass capture ratio of the ameliorated inlet at low Mach number (Ma=4,5) is much higher than the prototype inlet with almost the same total pressure recovery. At Ma=4, the mass capture ratio was enhanced 20.6%, and at Ma=5,1.5%. Besides of the mass capture ratio, the starting ability of the inlet is greatly improved. The experimental results show that the prototype inlet can only start at the attack angle of -2°, but the ameliorated inlet can start at the attack angle of +4°. Because the spillage amelioration was designed specially for the low Mach number flow, the performance of the ameliorated inlet was almost the same as the prototype inlet at high Mach number ( Ma=6,7). The research proves that reducing the spillage between the sidewalls and adding spillage on the down wall can greatly improve the performance of the side-compression hypersonic inlet. 

Key words: Side-compression hypersonic inlet；Spillage；Numerical simulation；Wind tunnel test

赵一龙,范晓樯,王翼,梁剑寒,王振国. 高超侧压进气道溢流方案的改进与分析[J]. 推进技术, 2013, 34(7): 873-879.

ZHAO Yi-long, FAN Xiao-qiang, WANG Yi, LIANG Jian-han, WANG Zhen-guo. Spillage Amelioration and Analysis of Side-Compression Hypersonic Inlet[J]. Journal of Propulsion Technology, 2013, 34(7): 873-879.

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