绕振动机翼非定常气动力迟滞特性的模拟研究

Research on the Hysteresis Properties of Unsteady Aerodynamics About the Oscillating Wings

Aircraft Engineering Department, Northwestern Polytechnical University, Xi'an 710072, P. R. China

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,研究了机翼绕不同转轴或以不同频率振动的非定常气动力迟滞特性.
- 非定常流动 /
- 迟滞特性 /
- 大迎角 /
- 旋涡流动
Abstract: In the work, I t is shown the numerical investigations about the unsteady inviscid results obtained for the pitching oscillating wings at different angles of at tack. The results are obtained by solving the unsteady Euler equations in a body-fit ted 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.
- unsteady flow /
- hysteresis /
- high angle of attach /
- vortical flow

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