三角翼大迎角非对称旋涡破裂数值模拟

Asymmetrical Vortex Breakdown of Delta Wings at High Incidence

采用由伪时间子迭代格式实现的二阶精度LU SGS方法进行时间推进,并以Jameson中心加人工粘性格式进行空间离散,应用层流假设和Baldwin Lomax(B L)模式,求解雷诺平均的薄层Navier Stokes(N S)方程组以模拟细长三角翼大迎角流动.为验证本方法,首先计算了具备实验数据的65°后掠角三角翼大迎角流场,获得令人满意的结果;然后模拟了80°后掠角的细长三角翼,研究其大迎角非对称旋涡破裂特性.

A fully implicit Lower-Upper-Symmetric-Gauss-Seidel (LU-SGS) with pseudo time sub-iteration and the modified Jameson's central scheme are applied to solve thin layer Navier-Stokes (N-S) equations with laminar hypothesis and Baldwin-Lomax (B-L) model for the vortical flows around delta wings at high angles of attack (AOA). To validate the codes, a 65 degree swept delta wing is computed in transonic cases, where M∞=0.85, α=10°, 20° and Re=5×106. Then asymmetrical vortex breakdown flows with M∞=0.3, and Re=1.3×106, at high AOA around a 80° swept delta wing are presented and discussed. The computational results are compared with experimental data available and good agreement is achieved.