摘要
利用数值模拟方法开展了机翼在不同条件下，由于俯仰振动引起的非定常气动力迟滞特性的模拟计算研究·根据有限体积方法对非定常欧拉方程进行数值求解，以确定相应问题的流场及气动力特性；同时，分别以具有ＮＡＣＡ＿００１２翼型的矩形机翼和带有６５°后掠角的三角翼为例。
In the work, It is shown the numerical investigations about the unsteady inviscid results obtained for the pitching oscillating wings at different angles of attack. The results are obtained by solving the unsteady Euler equations in a body_fitted coordinate system. It is based on the four_stage Runge_Kutta time stepping scheme. Meanwhile to increase the time step that is limited by Courant limit (CFL), the implicit residual smoothing with local variable parameters is used. As a result, the unsteady aerodynamics about a rectangular wing and a delta wing, which are oscillated in pitching with different frequencies, are shown in this paper. The properties of the unsteady aerodynamics in these cases are researched here.
出处
《应用数学和力学》
EI
CSCD
北大核心
1999年第8期835-846,共12页
Applied Mathematics and Mechanics
