一体化高超声速飞行器气动特性数值仿真  

Numerical simulation of integrated hypersonic vehicle's aerodynamic performance

作　　者：黄伟[1] 王振国[1] 

机构地区：[1]国防科学技术大学航天与材料工程学院,长沙410073

出　　处：《航空动力学报》2009年第6期1351-1356,共6页Journal of Aerospace Power

基　　金：国防科技大学优秀研究生创新项目(B070101);湖南省研究生创新项目(3206)

摘　　要：采用二维耦合隐式N-S(Navier-Stokes)方程和标准k-ε湍流模型对具有哈克外形头部的一体化高超声速飞行器在进气道关闭、发动机通流以及发动机点火状态下的升力特性、阻力特性、俯仰力矩特性以及升阻比特性进行了数值模拟,考察了机身头部长细比对其气动性能的影响,结果发现,在第一种定义方式下的飞行器构型气动性能改良程度明显高于第二种定义方式,同时,随着机身头部长细比的增加,一体化高超声速飞行器的气动性能得到明显提高,可以满足飞行器巡航时的气动要求.Two-dimension coupled implicit Naviers Stokes equations and standard k-ε viscid models were introduced to simulate the lift characteristic, drag characteristic, pitching moment characteristic and lift-to-drag ratio characteristic of integrated hypersonic vehicle with Hark head configuration working under the conditions of inlet closed, inlet open but unfired and inlet open and fired. The influence of head slenderness ratio on the aerodynamic performance was discussed. It is concluded that the improvement degree of aerodynamic per formance designed with the first method is greater than that designed with the second one, meanwhile, with the increasing of head slenderness ratio, the aerodynamic performance of integrated hypersonic vehicle becomes better in evidence, it can satisfy the aerodynamic requirement of cruising vehicles.

关 键 词：一体化高超声速飞行器 哈克外形头部 升力特性 阻力特性 俯仰力矩特性 升阻比特性 

分 类 号：V235.21[航空宇航科学与技术—航空宇航推进理论与工程]