流动减阻技术机理与应用现状  

Mechanism and Application Status of Flow Drag Reduction Technology

作　　者：徐柯哲 赵凌波 Xu Kezhe;Zhao Lingbo(Beijing Aerospace Technology Institute,Beijing 100074,China)

机构地区：[1]北京空天技术研究所,北京100074

出　　处：《战术导弹技术》2018年第6期20-25,69,共7页Tactical Missile Technology

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.

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 

分 类 号：TJ761.14[兵器科学与技术—武器系统与运用工程]