火箭推进2018，Vol.44Issue(2)：1-9,38,10.
前后缘同时可控的乘波体气动修型设计与分析
Aerodynamic modification design and analysis of waverider with controllable leading and trailing edges
摘要
Abstract
Based on the supersonic aerodynamic principle combined with the streamline tracing and geometric reconstruction technique,a design method of waverider with controlled the leading and trailing edge was developed in this paper.Under the conditions that the horizontal projection of leading edge is hyper elliptical and the trailing edge is circular,the aerodynamic modification waverider was designed by using this method.Numerical simulation results at design point(Ma=6.0)and relay point(Ma=4.0) indicate that the surface of aerodynamic modification waverider is of smooth transition while the leading and tailing edge are specified simultaneously,except a very small high pressure area at both sides of the exit.Therefore,it is able to maintain the wave structure and characteristics of original waverider.Com-pared with the original waverider,the volume ratio, life force and pre-compression efficiency of aerody-namic modification waverider are higher.In addition,the pitching moment is almost equal but the lift-drag ratio is decreased.Under the viscous condition, the lift-drag ratio decreases from 2.91 to 2.53 at design point and decreases from 2.69 to 2.32 at relay point.The above results correspond to the design expectation,and the design method is feasible.关键词
乘波体/气动修型/流线追踪/几何重构/投影形状Key words
waverider/aerodynamic modification/streamline tracing/geometric reconstruction/pro-jection shape分类
航空航天引用本文复制引用
李永洲,李光熙,张堃元,马元..前后缘同时可控的乘波体气动修型设计与分析[J].火箭推进,2018,44(2):1-9,38,10.基金项目
国家自然科学基金(11702205) （11702205）
