乘波体一体化特性的实验与计算研究  

The Experimental and Computational Study on Integration Characteristics of Waverider

作　　者：王玉玲[1] 高超[1] 肖虹[1,2] 

机构地区：[1]西北工业大学翼型、叶栅空气动力学国防科技重点实验室,西安710072 [2]湖南城市学院,湖南益阳413000

出　　处：《弹箭与制导学报》2014年第1期126-128,共3页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：文中对发动机/机身一体化乘波体外形的气动特性,采用SST湍流模型求解N-S方程进行了数值计算,并在FD-07风洞中进行了详细的测压试验验证。试验和计算的状态有Ma=6,α=-2°,0°,2°,4°,6°。结果表明:在计算状态下,计算与试验吻合良好,飞行器前体达到预压缩设计要求,进气道入口流动均匀,后体膨胀效果明显,并且保持了良好的气动特性。An optimized waverider based on wedge-cone flow was numerically simulated by equation N-S with SST turbulence model. Mach 6 application has been studied here for attack angle ranging from -2~ to 6~. The result was compared with experiment which measures pressure. Further, the aerodynamic characteristics analyses were conducted under both design condition and off-design conditions. It was shown here that computational simulation results were in good agreement with experimental results. The forebody pre-compress quality matched the design well, the flow was uniform at inlet of engine and quickly expanded at the aft body, moreover, the L/D kept satisfying aerodynamic characteristics.

关 键 词：乘波体 气动特性 测压试验 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]