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矩形转圆形高超声速内收缩进气道数值及试验研究
引用本文:南向军,张堃元,金志光,孙波.矩形转圆形高超声速内收缩进气道数值及试验研究[J].航空学报,2011,32(6):988-996.
作者姓名:南向军  张堃元  金志光  孙波
作者单位:1. 南京航空航天大学能源与动力学院,江苏南京,210016
2. 南京理工大学机械工程学院,江苏南京,210094
摘    要:采用压力梯度先增大后减小压升规律轴对称基准流场,结合流线追踪及截面渐变技术设计了矩形转圆形内收缩进气道模型,并采用4°斜楔模拟飞行器前体,对前体、进气道一体化模型进行了数值模拟和风洞试验,初步得到了该进气道的流场结构及总体性能.设计点和接力点的数值模拟结果表明该进气道可在马赫数Ma=4~6状态下正常工作,且具有良好的总...

关 键 词:高超声速进气道  基准流场  压升规律  数值模拟  风洞试验
收稿时间:2010-09-08;

Numerical and Experimental Investigation of Hypersonic Inward Turning Inlets with Rectangular to Circular Shape Transition
NAN Xiangjun,ZHANG Kunyuan,JIN Zhiguang,SUN Bo.Numerical and Experimental Investigation of Hypersonic Inward Turning Inlets with Rectangular to Circular Shape Transition[J].Acta Aeronautica et Astronautica Sinica,2011,32(6):988-996.
Authors:NAN Xiangjun  ZHANG Kunyuan  JIN Zhiguang  SUN Bo
Institution:1.College of Energy & Power Engineering,Nanjing University of Aeronautics and Astronautics, Nanjing 210016,China 2.School of Mechanical Engineering,Nanjing University of Science and Technology, Nanjing 210094,China
Abstract:With pressure gradient on the wall of the inlet’s basic flow field increasing at the front part then decreasing at the rear part, using streamline tracing and varying section techologies, a hypersonic inward turning inlet with rectangular to circular shape transition integrated into 4° wedge forebody, is designed and investigated with numerical simulation and experimental method. The flow field structure and performance of the inlet are primarily obtained. The simulation results of design points and take-over speeds indicate that this inlet can operate normally over the Mach number range of 4-6 and has good performance with 4° angle of attack. The inlet model is tested in a hypersonic wind tunnel at Mach number 6 with 4° angle of attack. And the experimental results indicate that the scaled inlet model’s total pressure recovery is 0.45. It can generate a compression ratio of 41.2 and withstand a back pressure ratio of 200 relative to tunnel static pressure.
Keywords:hypersonic inlets  basic flowfield  law of pressure rise  numerical analysis  wind tunnel test
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