跨音速机翼操纵面定常、非定常气动力计算

采用代数方法及椭圆型方程线松弛迭代优化方法生成三维ＣＨ贴体网格。用时间精确近似因式分解差分方法求解守恒型非定常全位势方程。操纵面偏转用物面当量法向速度模拟。考虑附面层影响，通过粘位迭代得到跨音速机翼操纵面的定常、非定常气动力。所得结果与实验数据相当吻合。

Computation of Steady and Unsteady Transonic Flow for a Wing with Control Surface Deflections

Algebraic methods and optimal elliptic partial differential equations are used to generate three dimensional C H boundary fitted grids. The conservatively full potential equation is solved by time accurate approximate factorization algorithm and internal Newton iterations. The control surface deflection is modeled by using an equivalent body velocity approach. A integral boundary layer method based on the dissipation integral is used to account for viscous efforts. The computational results about steady and unsteady transonic forces on control surface are in agreement with experimental data.