乘波体前体气动特性数值计算及实验验证  

Numerical and Experiment Study of Waverider Forebody Aerodynamic Characteristics

作　　者：禹彩辉[1] 高超[1] 耿卫民[1] 南江[1] 郑博睿[1] 

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,陕西西安710072

出　　处：《航空计算技术》2010年第5期75-78,共4页Aeronautical Computing Technique

摘　　要：对机身/发动机一体化构型的乘波体的气动特性进行了数值计算和分析,采用格心格式的有限体积方法求解雷诺平均N-S方程,对一体化构型的乘波体三维粘性流场进行了数值计算,同时对同一构型的测压模型进行高超声速测压风洞实验,计算结果与实验吻合良好。结果表明:乘波体具有高升力、低阻力及大升阻比特性,飞行器前体预压缩效果明显,气动特性良好。The aerodynamic characteristics of the airframe/scramjet engine integrated waverider is studied by numer- ical simulation. The paper simulates the three- dimensional viscid flow field of airframe/scramjet engine integrated waverider forebody, by computing Reynolds averaged Navier- Stokes equations with cell center type finite volume method. A hypersonic pressure experiment is made to validate the result of simulation. The results of experiment and computation show that：the simulation agree with the test date;waverider- derived hypersonic vehicle be characterized by high lift and low drag and high lift - drag ratio ; the pre- compressive performance of the forebody can satisfy the requirement of the in- let and it keeps good aerodynamic characteristics.

关 键 词：乘波体 预压缩 升阻比 测压实验 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]