低超声速来流中机翼跨声速非定常气动力数值解法  

A Numerical Method for Unsteady Transonic Aerodynamics About Wings at Low-Supersonic Freestreams

作　　者：张建柏[1] 张秀滨[1] 

机构地区：[1]中国空气动力研究与发展中心,四川绵阳621000

出　　处：《空气动力学学报》1993年第3期303-307,共5页Acta Aerodynamica Sinica

摘　　要：本文给出一种低超声速来流中机翼跨声速非定常流的计算方法。该方法使用跨声速小扰动理论,正确地计入了沿流向平面流动特征线的压力波的运动边界条件。流动方程是使用时间精确交替方向隐式(ADI)有限差分解法求解。试算了M=1.1的矩形翼和M=1.1、1.34的F5机翼的定常和非定常气动力,并与国外的风洞试验和计算结果作了比较,符合很好。表明本方法是有效的。A computational procedure is presented for predicting transonic unsteady flows about wings at low-supersonic freestreams.The method uses transonic small-perturbation theory. Supersonic freestreams are simulated by properly accounting for motion boundary conditions based on pressure waves along the flow characteristic lines in streamwise planes. The flow equations are solved using the time-accurate, alternating-direction implicit finite-difference scheme. Transonic steady and unsteady pressures arc computed for a rectangular wing at M = 1.1 and the F5 wing at M = l.1, 1.34. All computed results are compared well with the foreign wind-tunnel experimental data and computed results. The comparison shows that the present method is successful.

关 键 词：超音速流动 跨音速流动 机翼 

分 类 号：V211.41[航空宇航科学与技术—航空宇航推进理论与工程]