矢量喷管射流对机场道面气流参数的影响

On Effect of Nozzle Jet Flow on Runway Stream Parameters

用Runge-Kutta四步时间推进有限体积法,结合Baldwin-Lomax代数湍流模型求解了雷诺平均守恒形式的三维Navier-Stokes方程,计算了不同发动机喷管射流矢量角时机场道面的速度、压力和温度分布。计算结果表明,发动机射流矢量角对机场道面的速度、温度分布有很大影响。

When present-day fighter with vector nozzle takes off, the very high temperature and very high velocity of the nozzle jet flow is increasingly damaging to the runway. In this paper we present our research results on the effect of nozzle jet flow on runway stream parameters. Our theoretical study utilizes many well known and mature theoretical tools such as: three-dimensional Navier-Stokes equations, Reynolds-averaged unsteady flow, Baldwin-Lomax algebraic turbulence model, finite volume method, Runge-Kutta time stepping schemes. Our rather extensive but still limited computed results give two preliminary but important conclusions: (1) the highest temperature and the highest velocity of jet flow on the runway occur at points very near each other; (2) the highest temperature on the runway increases rapidly and nearly linearly with increasing vector angle.