无人机埋入式进气道气动特性数值仿真研究
Numerical Simulation of Aerodynamic Characteristics of Submerged Inlet for Unmanned Aerial Vehicle
肖毅 1马经忠 2沈亮 3胡杨2
作者信息
- 1. 中国民用航空江西航空器适航审定中心,江西 南昌 330098
- 2. 江西洪都航空工业集团有限责任公司,江西 南昌 330096
- 3. 江西航空研究院,江西 南昌 330098
- 折叠
摘要
埋入式进气道具有隐身性能好、飞行阻力低等优点,对提升无人机巡航经济性及战场生存能力具有重要意义.为了全面研究此类进气道的气动特性,在无人机概念布局下设计了埋入式进气道方案,并进行了数值仿真研究,重点分析了埋入式进气道性能随飞行速度、飞行迎角及出口马赫数的变化规律.计算结果表明,随着飞行速度逐渐增大,埋入式进气道总压恢复系数先逐渐提高后急剧降低,畸变指数DC60先减小后增大;在常用迎角范围内,随着迎角的增大,进气道总压恢复系数逐渐降低;在出口马赫数0.3～0.48的范围内,随出口马赫数的增加,进气道总压恢复系数略微提高,畸变指数DC60有所减小.
Abstract
Submerged inlet has the advantages of high stealth performance and low flight resistance,which is of great significance to improve the cruise economy and battlefield survivability.In order to comprehensively study the aerodynamic characteristics of this kind of inlet,a scheme of submerged inlet was designed under the concept layout of Unmanned Aerial Vehicle(UAV),and the numerical simulation was carried out.The results show that,with the increase of flight speed,the total pressure recovery coefficient of the submerged inlet increases first and then decreases sharply,and the distortion index DC60 decreases first and then increases.The total pressure recovery coefficient of inlet decreases with the increase of angle attack of in the range of common attack angle.The total pressure recovery coefficient of inlet improves slightly with the increase of the outlet Mach number between 0.3～0.48,and the distortion index DC60 decreases.
关键词
无人机/埋入式进气道/数值仿真/总压恢复系数/畸变指数Key words
UAV/submerged inlet/numerical simulation/total pressure recovery coefficient/distortion index引用本文复制引用
出版年
2024
NETL
NSTL
万方数据