摘要
本文介绍一种带操纵面机翼的非定常跨声速流的有限差分计算方法。采用的方程是三元非定常跨声速修正小扰动位势方程,使用时间积分法,求解格式是近似因式分解交替方向隐式(ADI)格式。使用这种方法计算了F-5机翼在来流马赫数为0.9和0.925时的定常气动力和操纵面振荡的非定常气动力。计算结果与国外的NLR试验结果和XTRAN3S方法的计算结果进行了比较,表明计算是成功的。
A numerical method is presented for predicting unsteady transonic aerodynamic flow about aircraft wings with control surface. The numerical procedure solves the unsteady transonic modified three-dimensional small perturbation equation by time accurate alternating direction implicit finite difference scheme. As a computational example, the steady and unsteady aerodynamic force of F-5 wing with control surface oscillations is considered. Solutions are presented for two Mach numbers, 0.9 and 0.925, and compared with the foreign experimental data and XTRAN3S method. The comparison is shown to be successful.
出处
《空气动力学学报》
CSCD
北大核心
1991年第3期338-343,共6页
Acta Aerodynamica Sinica
关键词
非定常流
操纵面
跨声速流
计算
unsteady flow, control surface, transonic, numerical method.
