后缘喷流对三角翼绕流影响的N-S方程数值分析  

Numerical Investigation of Trailing Edge Jet Effects on Flows Around Delta Wing Using Navier-Stokes Equations

作　　者：张正科[1] 汤寒松[1] 贾剑波 

机构地区：[1]北京航空航天大学宇航学院,北京100083

出　　处：《空气动力学学报》2000年第4期484-489,共6页Acta Aerodynamica Sinica

基　　金：航空科学基金资助项目!(96A5 10 12 )

摘　　要：本文用拟压缩性方法求解不可压流雷诺平均拟压缩N S方程组 ,对带有后缘喷流的三角翼粘性绕流进行了数值模拟 ,求解中采用了Beam -Warming隐式近似因子分解格式以及MML代数湍流模型。计算结果说明 ,后缘喷流使涡核压强降低 ,使涡核速度增大 ,从而对三角翼前缘分离涡有稳定作用 ,并能增大上翼面的负压值和下翼面的正压值 ,从而可以增加部分升力。计算结果还说明 。Incompressible Reynolds averaged Navier Stokes equations are solved using pseudo compressibility method for the simulation of incompressible flow over a delta wing with trailing edge jet at high angles of attack. The Beam Warming implicit approximate factorization scheme and MML algebraic turbulence model are utilized in the simulation. The computed results indicate that the trailing edge jet has an effect to decrease the pressure and increase the axial velocity of the vortex core. So it has the effect to stabilize the vortex flow and consequently it decreases the upper wing surface pressure and increases the lower wing surface pressure, hence to increase the lift of the wing. The results further indicate that when the area of the trailing edge jet exit hole is increased, or the jet is deflected downward, the above mentioned effects become stronger.

关 键 词：旋涡 三角翼绕流 后缘喷流 流场模拟 

分 类 号：V211.41[航空宇航科学与技术—航空宇航推进理论与工程]