摘要
针对阻力过大给飞行器带来的设计难度和使用成本问题,调研分析了当前减阻技术的流动机理与应用现状。结果表明,在减小激波阻力方面,主要将强激波变成弱激波系,或者优化压力分布,使总压差阻力最小;在减小摩擦阻力方面,在层流区通过维持最大表面积的顺压梯度延迟转捩,而在湍流区通过改变表面几何形态或者在流体中添加大分子物质,减弱湍流强度,以上分析可为低阻力气动外形设计方法的建立和发展提供了参考。
Aiming at the difficulty of design and cost of use of aircraft which is caused by excessive drag,the main drag reduction measures and their application effects were investigated. The results show that in order to reduce the shock resistance,the strong shock is transformed into a weak shock system,or the pressure distribution is optimized to minimize the total pressure differential resistance. In the aspect of reducing friction resistance,the turbulent intensity is weakened in laminar region by delaying transition through maintaining the barotropic gradient of the maximum surface area,and in turbulent region by changing the surface geometry or adding macromolecule substances in the fluid. The analysis provides a reference for the establishment and development of low drag aerodynamic contour design method.
作者
徐柯哲
赵凌波
Xu Kezhe;Zhao Lingbo(Beijing Aerospace Technology Institute,Beijing 100074,China)
出处
《战术导弹技术》
北大核心
2018年第6期20-25,69,共7页
Tactical Missile Technology
关键词
流动减阻
激波阻力
等离子体
零质量射流
多孔压力腔
涡流发生器
涂层减阻
drag reduction
shock wave drag
plasma
zero-mass flux jet
porous pressure chamber
vortex generator
coating drag reduction
