马赫数可控的方转圆高超声速内收缩进气道试验研究

doi:10.7527/S1000-6893.2016.0035

流行力学与飞行力学

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马赫数可控的方转圆高超声速内收缩进气道试验研究

李永洲^1,2, 张堃元¹, 孙迪³

1. 南京航空航天大学能源与动力学院, 南京 210016;
2. 中国航天科技集团公司西安航天动力研究所, 西安 710100;
3. 中国航天科技集团公司西安航天动力技术研究所, 西安 710025

收稿日期:2015-10-13 修回日期:2015-12-28 出版日期:2016-10-15 发布日期:2016-02-22
通讯作者: 李永洲,Tel.:029-85208061 E-mail:nuaa-2004@126.com E-mail:nuaa-2004@126.com
作者简介:李永洲男,博士,工程师。主要研究方向:高超声速推进技术和内流气体动力学。Tel.:029-85208061 E-mail:nuaa-2004@126.com;张堃元男,教授,博士生导师。主要研究方向:高超声速推进技术和内流气体动力学。Tel.:025-84892201-2100 E-mail:zkype@nuaa.edu.cn;孙迪女,硕士,工程师。主要研究方向:高超声速气动热动力学。Tel.:029-85208061 E-mail:sinda.y@163.com
基金资助:
国家自然科学基金（90916029，91116001 ）

Experimental investigation on a hypersonic inward turning inlet of rectangular-to-circular shape with controlled Mach number distribution

LI Yongzhou^1,2, ZHANG Kunyuan¹, SUN Di³

1. College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;
2. Xi'an Aerospace Propulsion Institute, China Aerospace Science and Technology Corporation, Xi'an 710100, China;
3. Xi'an Institute of Aerospace Propulsion Technology, China Aerospace Science and Technology Corporation, Xi'an 710025, China

Received:2015-10-13 Revised:2015-12-28 Online:2016-10-15 Published:2016-02-22
Supported by:
National Natural Science Foundation of China (90916029, 91116001)

摘要/Abstract

摘要：

基于反正切马赫数分布的弥散反射激波中心体轴对称基准流场，设计了方转圆内收缩进气道，并对其进行自由射流试验和数值仿真，获得该类进气道设计点的工作特性。试验结果表明：进气道顶板压力分布具有反正切曲线特征，总体性能优良且出口涡流区较小，上述设计方法可行有效。设计点时出口总压恢复系数达到0.561，增压比为26.2，临界反压约为135倍来流静压，对应的总压恢复系数为0.210。当带4°攻角时，进气道出口增压比增加49.6%的同时总压恢复系数降低了17.5%。

关键词: 内收缩进气道, 基准流场, 马赫数分布规律, 风洞试验, 截面渐变

Abstract:

Based on the axisymmetric basic flowfield with diffusing reflected shock center body and arc tangent Mach number distribution, an inward turning inlet with rectangular-to-circular transition is designed. The experiment on the wind tunnel and numerical simulation are conducted to obtain the operation characteristics of the design point. The experimental results indicate that the pressure distribution of the top wall is characterized by an arc tangent curve. The inlet is of good overall performance, and the vortex region is small. In conclusion, the design method proposed is feasible and efficient. For the design point, the total pressure recovery coefficient is 0.561 and the compression ratio is 26.2 at the exit section. The critical back pressure is about 135 times of the free stream static pressure, and the corresponding total pressure recovery coefficient is 0.210. With 4°attack angle, the compression ratio increases by 49.6% but the total pressure recovery coefficient decreases by 17.5% at the exit section.

Key words: inward turning inlets, basic flowfield, Mach number distribution, wind tunnel test, shape transition

中图分类号:

V231

李永洲, 张堃元, 孙迪. 马赫数可控的方转圆高超声速内收缩进气道试验研究[J]. 航空学报, 2016, 37(10): 2970-2979.

LI Yongzhou, ZHANG Kunyuan, SUN Di. Experimental investigation on a hypersonic inward turning inlet of rectangular-to-circular shape with controlled Mach number distribution[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016, 37(10): 2970-2979.

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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

马赫数可控的方转圆高超声速内收缩进气道试验研究

Experimental investigation on a hypersonic inward turning inlet of rectangular-to-circular shape with controlled Mach number distribution

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