摘要
吻切锥乘波构型是未来高超声速有动力巡航飞行器气动外形重要的设计参考。采用参数化设计方法实现了吻切锥乘波构型的设计,并利用工程估算的方法对构型的气动性能进行了分析;在多参数正交试验分析的基础上,开展了以升阻比,容积和容积率为目标的设计优化。CFD计算显示,优化的外形具有良好的升阻比和容积率性能,且底部流动均匀,是实现高超声速飞行器前体/超燃发动机进气道一体化的重要参考。
Osculating cone waverider configuration is an important design reference to the powered hypersonic vehicle.This paper parameterized the design process of OC waverider and engineering method was used to evaluate waverider＇s aerodynamic performances.Based on the orthogonal experiment,L/D ratio,volume and volume efficiency were chosen as optimized objective functions to optimize the configuration.CFD simulation shows that the optimized configuration has better L/D,volume,volume efficiency and uniform flow at the base,thus it is an important design reference in the hypersonic engine-airframe integration design.
出处
《国防科技大学学报》
EI
CAS
CSCD
北大核心
2007年第4期12-16,共5页
Journal of National University of Defense Technology
基金
国家863计划资助项目(2005AA756050)
国家自然科学基金项目(10302031)
关键词
吻切锥乘波构型
多目标
容积
容积率
osculating cone waverider
multi-object
volume
volume efficiency
