密切弯曲激波乘波体技术的应用及有效性分析
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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。
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%.
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%.
引文
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[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 Com-putational 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].AIAA2016-3288.
[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 Yuanyuan,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.