非均匀来流下等压力梯度曲面压缩系统的试验研究

推进技术 ›› 2013, Vol. 34 ›› Issue (12): 1593-1600.

• 气动热力学与总体技术 • 上一篇下一篇

非均匀来流下等压力梯度曲面压缩系统的试验研究

潘瑾¹,金峰²,张堃元²

南京航空航天大学金城学院,江苏南京211156;南京航空航天大学能源与动力学院,江苏南京 210016;南京航空航天大学能源与动力学院,江苏南京 210016

发布日期:2021-08-15
作者简介:潘瑾(1968—),女,博士,讲师(工程师),研究领域为流体力学。E-mail:pbrj@163.com
基金资助:
自然科学基金重大研究计划(90916029)。

Experimental Investigation of Constant Pressure Gradient Curved Compression System in Non-Uniform Inflow

College of Jincheng, Nanjing University of Aeronautics and Astronautics, Nanjing 211156, China;College of Energy and Power, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;College of Energy and Power, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

Published:2021-08-15

摘要/Abstract

摘要： 根据激波和膨胀波理论,设计了Ma=5.3等压力梯度曲面压缩系统。在Ma=3.85和Ma=5.3的小高超风洞完成均匀来流试验,并利用风洞壁面自然发展的附面层进行非均匀来流等压力梯度曲面压缩系统性能试验。试验发现:均匀来流下,试验模型壁面压力均按照等压力梯度规律分布,但来流马赫数Ma=5.3时出口流场均匀性较差；非均匀来流下,大量的附面层吸入不仅影响壁面压力不再呈等压力梯度分布,而且对出口流场均匀性影响也极大。 

关键词: 超声速进气道;曲面压缩;等压力梯度;弯曲激波;风洞试验 

Abstract: According to the shock wave and expansion wave theory, a model with constant pressure gradient curved compression system was designed at Ma=5.3. The curved compression model was tested in Ma=3.85and Ma=5.3wind tunnel at the condition of uniform inflow and simulated forebody boundary layer non-uniform inflow. The experimental results indicate that the pressure distribution of model surface are of constant pressure gradient feature in uniform inflows. The uniformity of outlet flowfield is worse at inflow Mach number Ma=5.3.The incoming flow non-uniformity has a dramatic effect on the pressure distribution of model surface and the uniformity of outlet flowfield. 

Key words: Supersonic inlets; Curved compression; Constant pressure gradient; Curved shock; Wind tunnel test

潘瑾,金峰,张堃元. 非均匀来流下等压力梯度曲面压缩系统的试验研究[J]. 推进技术, 2013, 34(12): 1593-1600.

PAN Jin¹,JIN Feng²,ZHANG Kun-yuan². Experimental Investigation of Constant Pressure Gradient Curved Compression System in Non-Uniform Inflow[J]. Journal of Propulsion Technology, 2013, 34(12): 1593-1600.

参考文献

[1] 王健, 李宏东,朱守梅,等.冲压发动机用轴对称进气道设计和试验[J].推进技术,2009,0(6):682-686.(WANG Jian, LI Hong-dong, ZHU Shou-mei,et al.Design and Wind Tunnel Test of an Axisymmetric Inlet for Ramjet Engine [J].Journal of Propulsion Technology, 2009,0(6):682-686.)
[2] 贺旭照, 乐嘉陵, 宋文燕,等.基于轴对称喷管的三维内收缩进气道的设计与初步评估[J].推进技术, 2010,1(2):147-152.( HE Xu-zhao ,LE Jia-ling,SONG Wen-yan,et al.3D Inward Turning Inlet Design Basing on Axisymmetric Nozzle and Its Preliminary Assessment[J].Journal of Propulsion Technology, 2010,1(2):147-152.)
[3] 刘凯礼,李博,雷雨冰,等.宽高比对二元高超声速进气道性能的影响[J].推进技术,2009,0(4):446-450.(LIU Kai-li,LI Bo,LEI Yu-bing,et al.Effect of Aspect Ratio on 2-D Hypersonic Inlet Performance[J].Journal of Propulsion Technology, 2009,0(4):446-450.)
[4] 张晓嘉,岳连捷,张新宇.大内收缩比二元高超声速进气道波系配置特性[J].推进技术,2012,3(4):505-509.(ZHANG Xiao-jia,YUE Lian-jie,CHANG Xin-yu.Shocks Arrangement of Ramp Compression Hypersonic Inlet with High Internal Contraction Ratio[J].Journal of Propulsion Technology,2012,3(4):505-509.)
[5] Hank Joseph M,Murphy James S,Mutzman Richard C． The X-51A Scramjet Engine Flight Demonstration Program[R]． AIAA 2008-2540．
[6] Ferlemann Shelly M,McClinton Charles R,Rock Ken E, et al． Hyper-X Mach 7Scramjet Design,Ground Test and Flight Results[R]．AIAA 2005-3322．
[7] Christopher D Karlgaard． Hyper-X Mach 10Trajectory Reconstruction[R]．AIAA 2005-5920．
[8] 金志光,张堃元.高超侧压式进气道简单唇口调节方案设计[J].推进技术,2008,9(1):43-48.(JIN Zhi-guang,ZHANG Kun-yuan.Concept of a Varied Geometry Scramjet Inlet with Rotatable Cowl[J].Journal of Propulsion Technology,2008,9(1):43-48.)
[9] 肖雅彬,岳连捷,龚鹏,等.三面压缩式高超声速进气道流动结构研究[J].实验流体力学,2008, 29(2):64-67.
[10] 孙波,张堃元,金志光,等.流线追踪Busemann进气道设计参数的选择[J].推进技术,2007,8(1):55-59.( SUN Bo,ZHANG Kun-yuan,JIN Zhi-guang,et al.Selection of Design Parameters for Streamtraced Hypersonic Busemann Inlets[J].Journal of Propulsion Technology, 2007,8(1):55-59.)
[11] 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,2006,7(3):252-256.(YOU Yan-cheng,LIANG De-wang,HUANG Guo-ping.Investigation of Internal Waverider-Derived Hypersonic Inlet[J].Journal of Propulsion Technology, 2006,7(3):252-256.)
[12] 潘瑾,张堃元,金志光.弯曲激波压缩型面的设计及数值分析[J].推进技术,2008,9(4):438-442.(PAN Jin, ZHANG Kun-yuan, JIN Zhi-guang.Design and Numerical Investigation of Curved Shock Compression Surface[J].Journal of Propulsion Technology, 2008,9(4):438-442.)
[13] 金志光, 张堃元.二维非常规压缩型面超/高超声速进气道的设计概念[J].推进技术,2004,25(3):226-229.(JIN Zhi-guang,ZHANG Kun-yuan.Concept of a Two-Dimensional Supersonic/Hypersonic Inlet with a Non-Conventional Compression Wall[J].Journal of Propulsion Technology,2004,25(3):226-229.)
[14] 潘瑾,张堃元.移动唇口变内收缩比侧压式进气道反压特性和自起动性能[J].航空动力学报,2009,4(1):104-109.
[15] Vinogradov V,Stepanov V,Alexadrovich E.Numerical and Experimental Investigation of Air Frame-Integrated Inlet for High Velocities[R].AIAA 89-2679.

非均匀来流下等压力梯度曲面压缩系统的试验研究

Experimental Investigation of Constant Pressure Gradient Curved Compression System in Non-Uniform Inflow

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