飞船返回舱高超声速气动特性的风洞实验分析

在返回舱再入过程中，高超声速配平升阻比是一个十分重要的参数。文章介绍球冠倒锥外形返回舱模型在φ0．5m高超声速风洞中气动力的测量结果，给出Ma=4．94、5．96、7．96，相应的Re=3×10^6、6×10^6、2×10^6（以最大横截面直径为特征长度）气流条件下，攻角从2°～-27°变化范围内返回舱的气动力特性，讨论重心位置纵移与横偏变化对配平升阻比和纵向稳定性的影响。

Wind-tunnel Test Analysis on Hypersonic Aerodynamic Characteristics of Returnable Module

During the re-entering of returnable module into the atmosphere, trim lift-to-drag ratio in the hypersonic region is a significantly important parameter. This paper describes the results of aerodynamic forces measurement for returnable module model in φ 0. 5m hypersonic wind tunnel. The testing Mach numbers are 4.94, 5.96 and 7.96 at Reynolds numbers of 3 × 10^6 ; 2 × 10^6 and 6 × 10^6 , based on taking the maximum diameter of model cross-section as characteristic length. The aerodynamic characteristics are given under angles of attack from 2° to -27°. The emphasis is put on the effect of the design displacements of the center of gravity upon the trim lift-to-drag ratio and the static stability.