高超声速乘波构型气动特性数值模拟研究  

Numerical Study of Hypersonic Waverider Configuration

作　　者：许少华[1] 陈小庆[1] 侯中喜[1] 夏智勋[1] 何烈唐[1] 

机构地区：[1]国防科学技术大学航天与材料工程学院,湖南长沙410073

出　　处：《航空计算技术》2008年第3期1-4,共4页Aeronautical Computing Technique

基　　金：国家自然科学基金项目(10302031)资助

摘　　要：乘波构型是突破常规"升阻比屏障"的有效途径,已成为高超声速飞行器设计的一种重要参考。在锥导和吻切锥乘波构型生成方法分析的基础上;针对两种设计外形开展了无粘和有粘气动性能的数值分析,获得了基本的气动性能参数。计算结果表明:锥导和吻切锥乘波构型不仅在设计状态下具有良好的升阻比特性,而且在较宽范围非设计状态下仍然具有良好的升阻比特性。锥导乘波构型容积率高,结构紧凑,可作为无动力滑翔式飞行器的设计参考;吻切锥乘波构型底部流动均匀,且外形调整方便,是超燃动力飞行器机身/进气道一体化构型的良好参考。Waverider is an effective way to break the ＂L/D barrier＂ and is an important design reference of the hypersonic vehicle. Based on the study of conical waverider and osculating cone waverider, CFD tool is used to analyze the aerodynamic performance of the two type waverider. The results show that both conical waverider and osculating cone waverider have good aerodynamic performances not only at design contidion but also at off-design conditions. Conical waverider＇s high volume efficiency and the compact architecture make it an reference of the unpowered glide vehicle＇s design. The osculating cone can offer not noly uniform flow field at the low surface but also it is easy to adjust the shape, thus is an well reference to the scramjet engine/airfram integration design.

关 键 词：高超声速飞行器 锥导乘波构型 吻切锥乘波构型 数值模拟 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]