摘要
在激波管风洞中,模型自由飞方法测量了两种不同迎风面三角翼体模型的大攻角气动力。应用局部方法以一种迎风面外形的实验结果为依据,估算了另一迎风面外形的气动特性,结果与实验值吻合较好。另外,本文还进一步估算了航天飞机外形的气动特性,与美国的 CALSPAN 公司48英寸(1.2米)激波风洞中的实验值相比,结果也令人满意。从而表明,局部方法和实验相结合。用于简捷快速估算任意外形的高超声速气动特性是一有效的工程预示方法。
Aerodynamic forces of Delta winged body with high angleof attack in two different windward configurations were measured byfree flight method in shock tunnel.The local method with the regimecoefficients derived from shock tunnel experimental results for oneconfiguration was applied to predicting the aerodynamic force coeffi-cients for the another configuration.The prediction agrees reasonably wellwith the experimental results Furthermore,the aerodynamic forcesprediction of space shuttle orbiter model by the local method also showsgood agreement with CALSPAN experimental results.
基金
国家自然科学基金
关键词
激波风洞
气动力
三角翼体模型
shock tunnel
aerodynamic forces measurement
local method
model free flight
delta winged body
