跨声速雷诺数效应的初步分析

本文概述了雷诺数Re效应的宏观表现,并从物理角度和边界层方程出发分析了Re数效应。研究表明,Re数效应根本上是通过干预边界层发展来实现的,集中体现在Re数对分离乃至更一般的激波与边界层相互作用区位置和范围的影响,这是Re数效应的一个本质方面。Re数对气动力参数,如俯仰力矩中心位置等的影响是通过这一途径实现的。此外,Re数效应的表现不是孤立的,在一定程度上受其他流动条件,如飞行马赫数(M)、物体形状等制约,据此本文提出了有关Re数效应控制的设想。

A Primary Study of Reynolds Number Effect in Transonic Flow

The macroscopic manifestations of Re Number Effect (ReNE) are summarized in this paper, and the analysis of the ReNE is made from physical insight and boundary layer equations. Examination shows that ReNE is essentially realized by interferring with evolution of boundary layer, which is collectively reflected in the influence of Re number on separation and, rather in general, on the location and scale of shock wave-boundary layer interaction region.This is an natural aspect of the ReNE, The influence of Re number on the gas dynamics parameters, for instance, the center location of pitching moment, is carried out by this approach. The action of the ReNE is not isolated, and to some extent, restricted by other flow conditions, such as flight Mach number, body shape and so on, from which an idea concerning the control of the ReNE is proposed in this paper.