摘要
针对设计马赫数为4的超音速巡航导弹用进气道的特点,选取混压式超声速轴对称冲压进气道,进气道外罩唇口的内型面采用椭圆形的型面设计。给出了设计方法。采用k-ω湍流模型,数值求解雷诺时均N-S方程,模拟得到了在不同飞行马赫数和不同反压条件下的流场结构、流动特征、设计参数和计算结果。有效地模拟了马赫数为4时设计工况与非设计工况条件下的流场性能,并给出了高马赫数内、外混合复杂流动的计算结果,可为弹用超声速巡航进气道的设计提供参考。
Accroding to the characteristic of a supersonic cruising missile＇s inlet,whose designed Mach number is 4.0, a mixed - compression supersonic axisymmetric ramjet inlet is adopted,the inner cowl surface of which is an elliptic surface. The design method is presented in this paper. The flow field structures, flow characteristics, design parameters and calculational results of different flight Mach numbers and different counter - pressures are obtained after the numberical simulation by using the k - ω turbulence model and the Reynolds - averaged Navier - Stokes equa- tions. The flow performances under on - design and off - design conditions are effectively simulated when the Mach number is 4. And the calculational results of high Mach number mixed complicated flow are presented. The results of this paper could provide references for the design of supersonic cruising missile＇s inlets.
出处
《计算机仿真》
CSCD
2008年第3期41-43,122,共4页
Computer Simulation
