密切弯曲激波乘波体技术的应用及有效性分析

推进技术 ›› 2018, Vol. 39 ›› Issue (2): 277-285.

密切弯曲激波乘波体技术的应用及有效性分析

卫锋,贺旭照,秦思,周正

中国空气动力研究与发展中心超高速空气动力研究所高超声速冲压发动机技术重点实验室，四川绵阳 621000,中国空气动力研究与发展中心超高速空气动力研究所高超声速冲压发动机技术重点实验室，四川绵阳 621000,中国空气动力研究与发展中心超高速空气动力研究所高超声速冲压发动机技术重点实验室，四川绵阳 621000,中国空气动力研究与发展中心超高速空气动力研究所高超声速冲压发动机技术重点实验室，四川绵阳 621000

发布日期:2021-08-15
作者简介:卫锋，男，硕士，研究实习员，研究领域为高超声速飞行器设计。E-mail: wf_nudt@hotmail.com 通讯作者:贺旭照，男，博士，研究员，研究领域为高超声速先进气动布局理论和应用。
基金资助:
国家自然科学基金(51376192)；高超声速冲压发动机技术重点实验室基金。

Application and Effectiveness Analysis of Wave-Rider Designed by Osculating Curve Shock（OCS） Flow-Field Method

Science and Technology on Scramjet Laboratory of Hypervelocity Aerodynamics Institute，CARDC，Mianyang 621000，China,Science and Technology on Scramjet Laboratory of Hypervelocity Aerodynamics Institute，CARDC，Mianyang 621000，China,Science and Technology on Scramjet Laboratory of Hypervelocity Aerodynamics Institute，CARDC，Mianyang 621000，China and Science and Technology on Scramjet Laboratory of Hypervelocity Aerodynamics Institute，CARDC，Mianyang 621000，China

Published:2021-08-15

摘要/Abstract

摘要： 将密切技术设计乘波体的应用推广至弯曲激波外锥流场中。针对不同激波形状(ICC)约束条件，在凸、凹激波曲外锥流场中，生成了四种构型的密切弯曲激波乘波体，采用数值模拟及理论分析的手段开展了密切弯曲激波乘波体技术应用的可行性验证及有效性分析。研究结果表明:(1)基于密切凸、凹激波外锥流场的乘波体乘波压缩面、出口截面压力分布、激波形状(ICC曲线)均与设计吻合，最大偏差小于5%，说明密切凸、凹激波外锥流场的方法设计乘波体是可适用的；(2)利用宽高比为0.5的超椭圆方程作为ICC控制曲线生成的乘波体，流场压力的理论解与数值解偏差可控制在1.6%以内，而宽高比为2的超椭圆方程作为ICC控制曲线生成的乘波体，流场压力偏差可控制在4%以内。

关键词: 密切技术；外锥流场；弯曲激波；乘波体；数值模拟

Abstract: The design of wave-rider by osculatinsg method have been extended into outer cone with curve shock flow-field. Under different constraint conditions of shock wave shape (ICC curve)， four configurations of wave-rider have been designed by osculating convex/concave shock (OCS) flow-field method. The feasibility verification and effectiveness analysis of this method have been studied by numerical and theoretical ways. The results show that: (1)The contours of wave-rider configurations at compression surface and exit plane， and the shock wave shape (ICC curve) derived from MOC theory and numerical simulation are in good agreement with each other， with pressure deviation less than 5%. It indicates that the OCS method is applicable to the design of wave-rider. (2)While the ICC curve chooses hyper-ellipse equation whose ratio of short and long axis is 0.5， the pressure deviation of MOC theory and numerical simulation can be smaller than 1.6%. While the ratio of short and long axis is 2， the pressure deviation of MOC theory and numerical simulation can be smaller than 4.0%.

Key words: Osculating method；Outer cone flow-field；Curve shock；Wave-rider；Numerical simulations

卫锋,贺旭照,秦思,周正. 密切弯曲激波乘波体技术的应用及有效性分析[J]. 推进技术, 2018, 39(2): 277-285.

WEI Feng,HE Xu-zhao,QIN Si,ZHOU Zheng. Application and Effectiveness Analysis of Wave-Rider Designed by Osculating Curve Shock（OCS） Flow-Field Method[J]. Journal of Propulsion Technology, 2018, 39(2): 277-285.

参考文献

[1] Lunan D. Wave-Rider,a Revised Chronology[R]. AIAA 2015-3529.
[2] Nonweiler T R F. Aerodynamic Problems of Manned Space Vehicles[J]. Journal of the Royal Aeronautical Society, 1959, 63: 521-528.
[3] Jones J G, Moore K C, Pike J, et al. A Method for Designing Lifting Configurations for High Supersonic Speeds, Using Axisymmetric Flow Fields[J]. Ingenieur-Archive, 1968, 37: 56-72.
[4] Corda S. Viscous Optimized Hypersonic Wave-Rider Designed from Flows over Cones and Minimum Drag Bodies[D]. College Park: University of Maryland, 1988.
[5] Mangin B, Benay R, Chanetz B, et al. Optimization of Viscous Wave-Riders Derived from Axisymmetric Power-Law Blunt Body Flows[J]. Journal of Spacecraft and Rockets, 2006, 43(5): 990-998.
[6] Sobiezczky H, Dougherty F C, Jones K. Hypersonic Wave-Rider Design from Given Shock Waves[C]. Maryland: First International Wave-Rider Symposium, 1990.
[7] Chauffour M L, Lewis M J. Corrected Wave-Rider Design for Inlet Applications[R]. AIAA 2004-0511.
[8] Chauffour M L. Shock-Based Wave-Rider Design with Pressure Corrections, and Computational Simulations[D]. College Park: University of Maryland, 2004.
[9] Lewis M J, Chauffour M L. Shock-Based Wave-Rider Designed with Pressure Gradient Corrections and Computational Simulations[J]. Journal of Aircraft, 2005, 42(5): 1350-1352.
[10] Patrick E Rodi. The Osculating Flow-Field Method of Wave-Rider Geometry[R]. AIAA 2005-0511.
[11] Liu C Z, Bai P, Chen B Y, et al. Rapid Design and Optimization of Wave-Rider from 3D Flow[R]. AIAA 2016-3288.
[12] HE Xu-zhao, NI Hong-li. Osculating Inward Turning Cone Design Methods and Performance Analysis[J]. ACTA SINICA 2011, 43(5): 879-985.
[13] 贺旭照, 倪鸿礼. 密切曲面锥乘波体-设计方法及性能分析[J]. 力学学报, 2011, 43(6): 1077-1082.
[14] He X Z, Le J L, Wu Y C. Design of a Curved Cone Derived Wave-Rider Fore-Body[R]. AIAA 2009-7423.
[15] Maurice J Zucrow, Joe D Hoffman. Gas Dynamics Volume (II)[M]. American: Library of Congress Cataloging, 1976.
[16] 卫锋, 贺旭照, 贺元元, 等. 三维内转式进气道双激波基准流场的设计方法[J]. 推进技术, 2015, 36(3): 358-364. (WEI Feng, HE Xu-zhao, HE Yuan-yuan, et al. Design Method of Dual-Shock Wave Basic Flow-Field for Inward Turning Inlet[J]. Journal of Propulsion Technology, 2015, 36(3): 358-364.)
[17] 卫锋, 贺旭照, 陈军, 等. 微修形异型转圆内转式进气道的设计与试验研究[J]. 推进技术, 2017, 38(6): 1218-1225. (WEI Feng, HE Xu-zhao, CHEN Jun, et al. Design and Experiment Study of Minimized Shape Transformation Inward Turning Inlet with Abnormity Entrance to Circle Exit[J]. Journal of Propulsion Technology, 2017, 38(6): 1218-1225.)
[18] 周正, 贺旭照, 卫锋, 等. 密切曲内锥乘波前体进气道低马赫数性能试验研究[J]. 推进技术, 2016, 37(8): 1456-1460. (ZHOU Zheng, HE Xu-zhao, WEI Feng, et al. Experimental Studies of Osculating Inward Turning Cone Wave-Rider Fore-Body Inlet(OICWI)at Low Mach Number Conditions[J]. Journal of Propulsion Technology, 2016, 37(8): 1456-1460.)
[19] 卫锋. 基于特征线理论的流线追踪内转向进气道设计方法研究[D]. 长沙:国防科学技术大学, 2012: 65-70.
[20] Nielsen J N. Missile Aerodynamics[M].New York: McGraw-Hill Book Co.Inc., 1960, 280-293.　　　　　　　　　　　　　*　收稿日期:2016-12-07；修订日期:2017-02-14。基金项目:国家自然科学基金(51376192)；高超声速冲压发动机技术重点实验室基金。作者简介:卫锋,男,硕士,研究实习员,研究领域为高超声速飞行器设计。E-mail: wf_nudt@hotmail.com通讯作者:贺旭照,男,博士,研究员,研究领域为高超声速先进气动布局理论和应用。E-mail: hexuzhao@sina.com(编辑:田佳莹)