Design of hypersonic inward turning inlets with basic flowfield using arc tangent curve law of pressure rise

NAN Xiang-jun; ZHANG Kun-yuan; JIN Zhi-guang

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Design of hypersonic inward turning inlets with basic flowfield using arc tangent curve law of pressure rise

更新时间：2026-07-07

- Design of hypersonic inward turning inlets with basic flowfield using arc tangent curve law of pressure rise
- Vol. 26, Issue 11, (2011)
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- Published：2011
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NAN Xiang-jun, ZHANG Kun-yuan, JIN Zhi-guang. Design of hypersonic inward turning inlets with basic flowfield using arc tangent curve law of pressure rise[J]. 2011, 26(11).
DOI：

NAN Xiang-jun, ZHANG Kun-yuan, JIN Zhi-guang. Design of hypersonic inward turning inlets with basic flowfield using arc tangent curve law of pressure rise[J]. 2011, 26(11). DOI：

摘要

采用反正切曲线压升规律设计了轴对称基准流场

该压升规律初始部分压缩较缓

可产生较弱的前缘激波

末尾部分压缩较缓

可产生较小的内收缩比

中间部分压缩量较大

主要对气流压缩.对该压升规律的3个系数进行了参数化研究

得到各系数对流场压缩效率

压缩量

以及重要几何参数的影响规律.基于该基准流场设计了圆形进口内收缩进气道

并进行了无黏及黏性数值研究.结果表明:采用该压升规律可以有效减小进气道前缘激波强度

提高压缩效率

同时具有较小的参考内收缩比

进气道在设计点和非设计点均具有良好的流量捕获特性和较高的压缩效率.

Abstract

Numerical simulation was performed to study the performance of axisymmetric basic flowfield with arc tangent curve law of pressure rise

helping to weaken the leading shock wave and reduce the reference internal contraction ratio.This curve has three parameters

whose effects on the performance parameters such as total pressure recovery

static pressure ratio

contraction ratio and internal contraction ratio were studied.Finally

a circular inward turning inlet with the basic flowfield was designed and numerically simulated to get the flow characteristics and total performance.The result shows this inlet has weak leading shock wave and small internal contraction ratio

as well as high mass capture ratio and compression efficiency both on design point and off design point.

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Related Author

NAN Xiang-jun

ZHANG Kun-yuan

JIN Zhi-guang

SUN Bo

CAO Si

LIU Bao-jie

HAN Shao-bing

ZHONG Jing-jun

Related Institution

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

Department of Aerospace Engineering,School of Mechanical Engineering, Nanjing University of Science and Technology

National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics,School of Jet Propulsion, Beijing University of Aeronautics and Astronautics

Marine Engineering College, Dalian Maritime University

School of Energy Science and Engineering, Harbin Institute of Technology

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