基于反正切曲线压升规律设计高超内收缩进气道

南向军; 张堃元; 金志光

基于反正切曲线压升规律设计高超内收缩进气道

基金项目: 国家自然科学基金(90916029)

计量
- 文章访问数: 1801
- HTML浏览量: 65
- PDF量: 63
- 被引次数: 0
出版历程
- 收稿日期: 2010-12-04
- 修回日期: 2011-07-15
- 刊出日期: 2011-11-28

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

摘要

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.
- 高超进气道 /
- 内收缩进气道 /
- 基准流场 /
- 压升规律 /
- 数值模拟
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.
- hypersonic inlets /
- inward turning inlets /
- basic flowfield /

HTML

参考文献(14)

[1]	Billig F S.SCRAM:a supersonic combustion ramjet missile .AIAA Paper 93-2329,1993.
[2]	Billig F S,Kothari A.Streamline tracing:a technique for designing hypersonic vehicles[J].Journal of Propulsion and Power,2000,10(3):465-471.
[3]	Walker S H,Rodgers F.Falcon hypersonic technology overview .AIAA 2005-3253,2005.
[4]	Tam C J,Baurle R A,Streby G D.Numerical analysis of streamline-traced hypersonic inlets .AIAA Paper 2003-0013,2003.
[5]	孙波,张堃元,金志光.流线追踪Busemann 进气道马赫数3.85实验研究[J].航空动力学报,2007,22(3):396-399. SUN Bo,ZHANG Kunyuan,JIN Zhiguang.Experimental research of Mach 3.85 performance of a streamline traced hypersonic busemann inlet[J].Journal of Aerospace Power,2007,22(3):396-399.(in Chinese)
[6]	Mlder S,Szpiro J.Busemman inlet for hypersonic speeds[J].Journal of Spacecraft and Rockets,1966,3(8):1303-1304.
[7]	Drayna T W,Nompelis I,Candler G V.Hypersonic inward turning inlets:design and optimization .AIAA Paper 2006-0297,2006.
[8]	Matthews A J,Jones T V.Design and test of a modular waverider hypersonic intake .AIAA 2005-3379,2005.
[9]	Smart M K.Design of three-dimensional hypersonic inlets with rectangular to elliptical shape transition .AIAA 98-0960,1998.
[10]	尤延铖,梁德旺,黄国平.一种新型内乘波式进气道初步研究[J].推进技术,2006,27(3):252-256. YOU Yancheng,LIANG Dewang,HUANG Guoping.Investigation of internal waverider-derived hypersonic inlet[J].Journal of Propulsion Technology,2006,27(3):252-256.(in Chinese)
[11]	Barkmeyer D E F,Starkey R P,Lewis M J.Inverse waverider design for inward turning inlets . AIAA 2005-3915,2005.
[12]	Smart M K,Trexler C A.Mach 4 performance of a fixed-geometry hypersonic inlet with rectangular-to-elliptical shape transition .AIAA 2003-0012,2003.
[13]	Jacobsen L S,Tam C J,Behdadnia R.Starting and operation of a streamline-traced busemann inlet at Mach 4 .AIAA 2006-4508,2006.
[14]	南向军,张堃元,金志光,等,压升规律可控的高超声速内收缩进气道设计 [J].航空动力学报,2011,26(3):518-522. NAN Xiangjun,ZHANG Kunyuan,JIN Zhiguang,et al.Investigation on hypersonic inward turning inlets with controlled pressure gradient[J].Journal of Aerospace Power,20011,26(3):518-522.(in Chinese)