摘要
发展了一种基于分析法的高超声速乘波构型飞行器前体设计方法。运用该方法,设计了Ma=6.0具有三道封闭激波适用于匹配矩形高超进气道的乘波前体构型。对前体构型设计、非设计状态进行了全三维流场计算。计算结果显示:在设计状态下,前体构型具有优良的封闭激波性能,验证了设计方法的有效性;该前体在Ma=5.0~7.0、攻角-2°^+8°的范围内均具有良好的封闭激波性能。所设计的乘波前体在考虑进气道捕获能力的前提下,在-5°攻角下进气道总压恢复达到最大值。并且在-5°^+10°攻角范围内均有较高的总压恢复。
A new method of quickly generating hypersonic waverider forebody configurations was developed. A hypersonic forebody with three attached shockwave （in the design flight condition Ma=6.0） was designed. To better understand the forebody performance, three-dimensional flow field calculation of the waverider forebody was conducted in the design and off design conditions. The computational results show that the forebody has three attached shockwave in the design condition and the attached shockwaves exist when the flight mach number is about Ma= 5.0-7.0 and the attack angle -2° -＋8°. Considering the forebody＇ s capture ability, the waverider forebody can get its highest recovery coefficient of total pressure at 5° attack angle and it can get good recovery coefficient of total pressure at about -5°-＋ 10° attack angle flight condition.
出处
《弹箭与制导学报》
CSCD
北大核心
2008年第4期172-174,189,共4页
Journal of Projectiles,Rockets,Missiles and Guidance
基金
航天科技创新基金
西北工业大学科技创新基金
西北工业大学青年科技创新基金资助
关键词
乘波构型
前体
封闭激波
三维流场计算
高超声速
waverider
forebody
attached shock wave
three-dimensional flow field calculation
hypersonic
