摘要
采用Ｃ－Ｈ型网格、守恒型非定常全位势方程的时间精确近似因式分解差分法计算二维、三维的跨声速非定常位势流。用准定常、准二维方法计算边界层位移厚度，通过粘位迭代得到跨声速翼型、机翼的非定常气动力。所得结果与实验数据吻合很好。
The conservative full potential equation and C H grid are used to compute the unsteady transonic flows around airfoils and wings.The equation is solved by time accurate approximate factorization algorithm and internal Newton iterations.A flux biasing technique is applied to generate proper forms of the artificial viscosity to capture shocks.The wake is modeled by solving the unsteady vorticity convection equation.A 2D integral boundary layer method based on the dissipation integral is used to account for viscous efforts.Calculations are presented for NLR7301 airfoil and LANN wing.All results are in agreement with experimental data.
出处
《空气动力学学报》
CSCD
北大核心
1998年第4期461-467,共7页
Acta Aerodynamica Sinica
