基于重叠场源法的非定常气动力计算研究

Calculation of Unsteady Aerodynamics Using Overset Field-Panel Method

面向气动弹性工程应用,将基于雷诺平均N-S方程的定常流动数值解引入跨声速小扰动方程,在小扰动条件下非定常激波效应由定常激波效应确定,从而发展了一种可用于跨声速流动的非定常气动力计算方法。数值算法利用块三对角近似技术大大提高了算法的计算效率、节省了计算所需内存空间,并采用了重叠场源策略为复杂构型的非定常气动力计算提供了有利保障。文中以F5机翼为计算算例,研究了场源模型参数对非定常气动力计算结果的影响,并验证了块三对角近似算法的可靠性;以CRM WBH翼身尾构型为算例,检验了针对复杂构型重叠场源策略的可行性。

The paper present a method of calculating unsteady aerodynamics in transonic flow,in which steady flow solution based on RANS solver code are imported into transonic small disturbance equations,thus,the unsteady shock location is dominated by the steady shock location in the small amplitude sense. Block-tridiagonal approximation is used to improve the computational efficiency and save the memory,and the overset field panel scheme is developed for complex configuration to calculate unsteady aerodynamics. Taking F5 wing as an example,the effect of parameters of field-panel model on the calculated results of unsteady aerodynamics is investigated, and the reliability of block-tridiagonal approximation is validated. In addition,the validation of overset field-panel scheme is performed by comparing the results between the one block modeling and the overset modeling.