为研究飞行速度对内埋式航炮膛口流场特性的影响,基于Navier-Stokes方程和k-ε湍流模型,采用Roe格式分别 对4种飞行速度条件下的菱形机翼中内埋航炮膛口流场发展过程进行了数值模拟,对比分析了静止条件和超音速飞行状态下膛口流场的基本特征以及冲击波强度变化关系.结果表明:超音速飞行时形成由火药燃气冲击波、分离激波、滑移面等波系构成的膛口流场结构;在一定飞行速度范围内分离激波尺寸与来流马赫数正相关;膛口附近冲击波超压峰值变化与飞行马赫数有关.%In order to study the influence of flight velocity on the muzzle flow field characteristics of embedded gun, the field development processes in four different conditions are numerically simulated based on the Navier-Stokes equations and the k-ε turbulence model. The basic characteristics of the muzzle flow field under static condition and supersonic flight condition are compared, and the changes of blast intensity are analyzed. The result shows that the muzzle flow field structure of embedded aircraft gun during the supersonic flight includes propellant gas shock wave, separation shock wave, slip surface and so on; the magnitude of separation shock wave at a certain flight velocity is positively correlated with the Mach number; and the peak overpressure of blast changes with the Mach number.
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