临近空间高超声速飞行气动外形设计初探  

General Research on Aerodynamic Design of Hypersonic Near-Space Aircraft

作　　者：左艳辉[1] 

机构地区：[1]海军驻南昌地区航空军事代表室,江西南昌330024

出　　处：《教练机》2014年第4期60-64,共5页Trainer

摘　　要：根据临近空间大气特点、对临近空间高超声速飞行器的乘波体外形设计进行了初步探讨。论文介绍了乘波构型的概念和生成方法、基于楔形流场进行了两种∧型乘波体的外形设计,并且完成了数值模拟以及计算分析。数值模拟的结果验证了基于楔形流场∧型乘波外形设计方法和设计过程的可行性,为临界空间高超声速飞行器气动外形设计提供了参考。This paper launches a general research on aerodynamic design of hypersonic Near-Space aircraft in the unique atmospheric conditions. Besides, it presents the concept and creation of wave rider, and designs two different ∧-shaped wave riders based on wedge shaped flux field. Furthermore, it finished the numerical simulation, calculation and analysis on these wave riders. The result of numerical simulation shows feasibility and validity of the aerodynamic design based on wedge shaped flux field,and provides a foundation of aerodynamic design of hypersonic Near-Space aircraft in the future.

关 键 词：临近空间 高超声速 ∧型乘波体 数值模拟计算 

分 类 号：V221.3[航空宇航科学与技术—飞行器设计]