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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 ,喷口面积加大或喷流下偏会使上述作用增强
In this paper, the non-compressible Reynolds-averaged quasi-compressed NS equations are solved by the method of quasi-compressibility, and the viscous flow around the delta wing with trailing-edge jet is numerically simulated. The Beam -Warming implicit approximate factorization format MML algebraic turbulence model. The calculation results show that the trailing edge jet reduces the pressure of the vortex core and increases the velocity of the vortex core, thus stabilizing the separation vortex at the leading edge of the delta wing and increasing the negative pressure value of the upper airfoil and the positive pressure of the lower airfoil Pressure value, which can increase part of the lift. Calculation results also show that the spout area increases or jet bias will make the above-mentioned role enhanced