固体火箭技术2011，Vol.34Issue(1)：52-56,60,6.
凹腔结构对圆形超燃冲压发动机燃烧室阻力特性影响
Cavity configuration effect on drag characteristic of round scramjet combustor
摘要
Abstract
As one of the most effective methods to promote the fuel and the incoming air in the combustor to mix and combust steadily, the research of cavity has drawn an ever increasing attention. The effect of cavity configuration parameters on drag characteristic of round scramjet combustor was discussed by using numerical simulation method. Meanwhile, the effect of the angle of attack on the drag characteristic of the cavity was investigated preliminarily. The results show that the frictional drag of cavity is much less than its pressure drag, the drag of cavity on combustor mainly embodies its pressure drag characteristic; with the increasing of sweep-back angle, the drag of cavity decreases gradually under the conditions of engine ignition and cold flow. With the increasing of the ratio of the length to the depth, the drag of cavity increases at first, then decreases under the condition of engine ignition, but under the condition of cold flow, the drag decreases gradually. When the angle of attack is between -3° ～ 3°, the drag of the cavity is obviously larger under the condition of engine ignition. It would make a great difference to the further design of round scramjet combustor.关键词
圆形超燃冲压发动机燃烧室/凹腔/阻力特性Key words
round scramjet combustor/cavity/drag characteristic分类
航空航天引用本文复制引用
黄伟,雷静..凹腔结构对圆形超燃冲压发动机燃烧室阻力特性影响[J].固体火箭技术,2011,34(1):52-56,60,6.基金项目
国防科技大学优秀研究生创新资助项目(No.B070101) （No.B070101）
湖南省研究生科研创新资助项目(No.3206). （No.3206）
