摘要
试验研究了低密度环境下小发动机喷管高空羽流对平板模型的撞击效应。试验在高超声速低密度风洞中进行,试验气体选为氮气。对3个不同几何形状的小发动机喷管的共40个试验状态进行了测量,测出了平板模型上的表面压力分布,并对试验结果进行了初步分析。文章为研究数值模拟高空羽流撞击效应提供了试验证据。
Experimental study is performed for the plume impingement effect of small thruster on a flat plate under high altitude rarefied environment.The whole experimentation is conducted in the supersonic low density wind tunnel and the test gas is nitrogen. Forty experimental cases are measured for three different conical small thruster nozzles and different plate's locations.The plate's surface pressure is obtained.Primary analysis is carried out for the experimental results.The study provides the experimental foundation for research the plume impingement effect.
出处
《航天器环境工程》
2005年第2期86-91,共6页
Spacecraft Environment Engineering
基金
国防预研项目(41320060102)
关键词
低密度
高空羽流
撞击效应
气动力
low density
high altitude plume
impingement effect
surface force
