侧板构型对高超侧压进气道起动性能的影响

推进技术 ›› 2014, Vol. 35 ›› Issue (2): 145-150.

• 气动热力学 • 下一篇

侧板构型对高超侧压进气道起动性能的影响

赵一龙,范晓樯,梁剑寒,王振国

国防科技大学高超声速冲压发动机技术重点实验室,湖南长沙 410073;国防科技大学高超声速冲压发动机技术重点实验室,湖南长沙 410073;国防科技大学高超声速冲压发动机技术重点实验室,湖南长沙 410073;国防科技大学高超声速冲压发动机技术重点实验室,湖南长沙 410073

发布日期:2021-08-15
作者简介:赵一龙(1986—),男,博士生,研究领域为高超声速推进技术。E-mail:zhaoyilong2007@126.com
基金资助:
国家自然科学基金(11372347)。

Impacts of Sidewall Geometry on Starting Characteristics of Side-Compression Hypersonic Inlet

Science and Technology on Scramjet Laboratory,National University of Defense Technology,Changsha 410073,China;Science and Technology on Scramjet Laboratory,National University of Defense Technology,Changsha 410073,China;Science and Technology on Scramjet Laboratory,National University of Defense Technology,Changsha 410073,China;Science and Technology on Scramjet Laboratory,National University of Defense Technology,Changsha 410073,China

Published:2021-08-15

摘要/Abstract

摘要： 为了考察侧板构型对高超侧压进气道起动性能的影响,对相同收缩比下侧板分别为前掠和后掠构型的进气道开展了Ma=4来流下的风洞实验及相应的数值模拟研究。实验结果表明,侧板后掠进气道的起动性能优于侧板前掠构型,实验中侧板后掠进气道能够在+2°攻角时实现起动,而侧板前掠进气道仅能在-2°攻角时起动。对流场进行的数值模拟结果表明,侧板后掠进气道不但比侧板前掠进气道具有更高的内收缩段入口马赫数,而且交汇后的侧板激波与底板边界层干扰的强度较弱,使得边界层不易分离,两方面因素共同作用使得侧板后掠进气道的起动性能显著优于侧板前掠构型。 

关键词: 高超声速进气道;侧板;起动性能;数值模拟;风洞实验 

Abstract: In order to investigate the impacts of sidewall geometry on the starting characteristics of the side-compression hypersonic inlet, one inlet with forward-swept sidewall and another with aft-swept sidewall having the same contraction ratio were tested in a Ma=4wind tunnel and the flow field was researched by CFD. The experimental results show that the inlet with aft-swept sidewall exhibits better capability of starting, which can start at the attack angle of +2°, comparing with the forward-swept sidewall inlet starting at the attack angle of -2°. The numerical results show that the Mach number of the lip surface of the aft-swept sidewall inlet is higher than that of the forward-swept sidewall inlet, and the intensity of the interaction between the intersected sidewall shock and the boundary layer of the bottom wall is much weaker, which is propitious for suppressing the separation of the bottom boundary layer. The above two reasons jointly account for the fact that the aft-swept sidewall is good for the side-compression hypersonic inlet to start. 

Key words: Hypersonic inlet；Sidewall；Starting characteristics；Numerical simulation；Wind tunnel test

赵一龙,范晓樯,梁剑寒,王振国. 侧板构型对高超侧压进气道起动性能的影响[J]. 推进技术, 2014, 35(2): 145-150.

ZHAO Yi-long,FAN Xiao-qiang,LIANG Jian-han,WANG Zhen-guo. Impacts of Sidewall Geometry on Starting Characteristics of Side-Compression Hypersonic Inlet[J]. Journal of Propulsion Technology, 2014, 35(2): 145-150.

参考文献

[1] 王振国, 梁剑寒, 丁猛, 等.高超声速飞行器动力系统研究进展[J].力学进展, 2009,9(6):716-739.
[2] Holland S D, Perkins J N.Inviscid Parametric Analysis of Three-Dimensional Inlet Performance[J].Journal of Aircraft, 1994,1(3):610-620.
[3] 金志光, 张堃元.典型二元高超声速进气道与侧压式进气道的性能比较[J].航空动力学报, 2008,3(9):1553-1560.
[4] 贾地, 范晓樯, 冯定华, 等.高超声速侧压式进气道溢流特性研究[J].航空动力学报, 2007,2(1):85-89.
[5] Goonko Y P, Latypov A F, Mazhul I I, et al.Structure of Flow Over a Hypersonic Inlet with Side Compression Wedges[J].AIAA Journal, 2003,1(3):436-447.
[6] 范晓樯, 李桦, 易仕和, 等.侧压式进气道与飞行器机体气动一体化设计及实验[J].推进技术, 2004,5(6):499-502.(FAN Xiao-qiang, LI Hua, YI Shi-he, et al.Experiment of Aerodynamic Performance for Hypersonic Vehicle Integrated with Sidewall Compression Inlet[J].Journal of Propulsion Technology, 2004,5(6):499-502.)
[7] Holland S D.An Experimental Parametric Study of Geometric, Reynolds Number and Ratio of Specific Heats Effects in Three-Dimensional Sidewall Compression Scramjet Inlets at Mach 6[R].AIAA 93-0740.
[8] Holland S D.Mach 10Experimental Database of a Three-Dimensional Scramjet Inlet Flow Field[R].NASA-TM-4686, 1995.
[9] Hberle J, Gülhan A.Experimental Investigation of a Two-Dimensional and a Three-Dimensional Scramjet Inlet at Mach 7[J].Journal of Propulsion and Power, 2008,4(5):1023-1034.
[10] Gruhn P, Gülhan A.Experimental Investigation of a Hypersonic Inlet with and Without Sidewall Compression[J].Journal of Propulsion and Power, 2011,7(3):718-729.
[11] Liang J H, Fan X Q, Wang Y, et al.Performance Enhancement of Three-Dimensional Hypersonic Inlet with Sidewall Compression[J].Journal of Aerospace Engineering, 2008,2(8):1211-1219.
[12] 丁猛, 梁剑寒, 刘卫东, 等.碳氢燃料超燃冲压发动机进气道与燃烧室匹配性能试验研究[J].航空学报, 2005,6(1).
[13] 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, ZHAN Kun-yuan.Concept of a Varied Geometry Scramjet Inlet with Rotatable Cowl[J].Journal of Propulsion Technology, 2008,9(1):43-48.)
[14] 卫永斌, 张堃元.三维侧压式高超声速进气道阻力特性分析[J].航空动力学报, 2009,4(7):1594-1600.
[15] 李桦, 贾地, 范晓樯, 等.高超侧压进气道前/后掠的数值分析和比较[J].推进技术, 2007,8(1):65-67.(LI Hua, JIA Di, FAN Xiao-qiang, et al.Calculation and Comparison of Forward/Backward Swept Sidewall Compression Scramjet Inlets[J].Journal of Propulsion Technology, 2007,8(1):65-67.)
[16] Rodi P E, Trexler C A.The Effect of Bodyside Compression on Forward and Afterward Swept Sidewall Compression Inlets at Mach 4[R].AIAA 94-2708.
[17] Van Wie D M, Kwok F T, Walsh R F.Starting Characteristics of Supersonic Inlets[R].AIAA 96-2914.
[18] 梁徳旺, 袁化成, 张晓嘉.影响高超声速进气道起动能力的因素分析[J].宇航学报, 2006,7(4):714-719.
[19] 王翼, 范晓樯, 梁剑寒, 等.三维侧压高超声速进气道不起动流场试验与数值模拟研究[J].宇航学报, 2008,9(6):1927-1931.
[20] Panaras A G.Review of the Physics of Swept-Shock/Boundary Layer Interactions[J].Progress in Aerospace Sciences, 1996,2(2):173-244.

侧板构型对高超侧压进气道起动性能的影响

Impacts of Sidewall Geometry on Starting Characteristics of Side-Compression Hypersonic Inlet

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