摘要
用动量定理和激波论分析方法,推导出了横向喷入超音速主气流之内的等效体数学模型的弓形激波方程。给出了计算横向喷流气动干扰力的数学方法。该方法是一种近似理论方法,其结果与风洞试验数据很接近。给出的等效模型和弓形激波方程,对带有横向喷流的风洞试验设计是有益的。
From momentum theorem and the method of shock wave analysis,a mathematical model of e- quivalent body and a bow shock wave equation with transverse jet stream injecting into supersonic main stream are deduced in this paper. Furthermore,a mathematical method calculating the aerodynamic disturbing force of transverse jet stream is presented. It is an approximate theoretic method with simular result to the data of wind tunnel test. The equivalent body model and the bow shock wave equation presented here are available to the design of wind tunnel test with transverse jet stream.
出处
《战术导弹技术》
1995年第2期10-17,共8页
Tactical Missile Technology
关键词
横向喷流
气动力计算
导弹
扰动
面对面导弹
Transverse jet stream
Aerodynamic calculation
Ground to Ground missile Disturbance.
