振荡机翼跨音速非定常粘性绕流的数值计算

THE NUMERICAL CALCULATION OF TRANSONIC UNSTEADY VISCOUS FLOWS AROUND THE OSCILLATING WING

以非定常ＮＳ方程为主管方程，采用ＬＵＮＮＤ混合差分格式，Ｃ和ＣＨ型贴体运动网格，ＢＬ双层代数紊流模型，求解绕振荡翼型和三维机翼的跨音速非定常粘性流场。分别计算了ＮＡＣＡ００１２翼型和Ｍ６机翼作俯仰振荡时跨音速非定常粘性绕流流场。研究了非定常绕流的气动特性。部分计算结果和风洞实验值作了比较。

A numerical method is presented for calculating the unsteady transonic viscous flows around oscillating aerofoil and wing based on the unsteady Navier stokes equations. It adopts an implicit NND algorithm and Baldwin Lomax turbulence model in solving procedure.The computational grid is C and C H types in a body fitted coordinate system generated by an algebraical method.The transonic viscous flows around the NACA 0012 aerofoil and M6 wing with pitching oscillation have been calculated.Numerical results are in good agrement with experimental data.