超声速对流推力矢量喷管的数值模拟

Numerical simulation of fluidic counterflow thrust vectoring nozzle in supersonic flow

利用二次流对流剪切激励主射流方式来产生射流对流推力矢量方法是一种效率很高的矢量化喷流新方法,又称为对流推力矢量法。本文运用三阶精度MUSCL TVD有限体积格式求解二维非定常、可压缩、雷诺平均N-S方程和Spalart-Allmaras湍流模型,计算了对流推力矢量喷管的超声速射流问题,获得几种不同二次流吸气压强下对狭缝和喷管肩部壁面压强分布、剪切层诱导旋涡的结构特征和主射流矢量角等结果,计算结果与实验数据对比取得良好的一致性,并对计算结果进行了详细分析和讨论。

There is a new effectiveness method to vector the nozzle jet, also referred to be as counterflow thrust vectoring, which is generated by counterflow shear from the secondary stream influencing on primary jet. At present, in order to compute the problem about counterflow thrust vectoring nozzle in supersonic flows, two-dimensional unsteady compressible Reynolds averaged Navier-Stokes equations with Spalart-Allmaras turbulent mode are solved by using the MUSCL type TVDscheme with third order accuracy in finite volume method. The numerical results including pressure distributions on slot wall and primary nozzle collar, vortices structures induced by shear layer and primary jet vectoring angles under different suction pressure of secondary stream conditions are obtained. The computed results agree well with existed experimental data. In addition, the results here are analyzed and discussed in detail.