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高超声速飞行器后体喷管三维构型设计
引用本文:徐大军,陈兵,蔡国飙,徐旭. 高超声速飞行器后体喷管三维构型设计[J]. 航空动力学报, 2009, 24(2): 247-254
作者姓名:徐大军  陈兵  蔡国飙  徐旭
作者单位:北京航空航天大学宇航学院,北京,100191;北京航空航天大学宇航学院,北京,100191;北京航空航天大学宇航学院,北京,100191;北京航空航天大学宇航学院,北京,100191
摘    要:为研究高超声速飞行器后体喷管三维构型的设计,以NASA半壁喷管试验为参考,进行了二维及三维内外流相互作用的数值模拟计算,分析了后体喷管三维流场的特点.从高超声速飞行器机身推进一体化的角度,构建了后体喷管三维构型,进行了不同构型设计对后体喷管性能影响的参数研究.结果表明:后体喷管的三维效应不可忽视,后体喷管侧壁的存在及下壁面长度对性能影响较大. 

关 键 词:高超声速飞行器  一体化设计  后体喷管  三维构型  数值模拟
收稿时间:2008-01-22
修稿时间:2008-06-02

Design of three dimensional afterbody/nozzle configuration of airbreathing hypersonic vehicle
XU Da-jun,CHEN Bing,CAI Guo-biao and XU Xu. Design of three dimensional afterbody/nozzle configuration of airbreathing hypersonic vehicle[J]. Journal of Aerospace Power, 2009, 24(2): 247-254
Authors:XU Da-jun  CHEN Bing  CAI Guo-biao  XU Xu
Affiliation:School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China
Abstract:Three dimensional configuration design of afterbody/nozzle was studied in this paper.Flow filed numerical simulations were conducted on NASA single expansion ramp nozzle experiment model.Numerical simulation results of two-dimensional and three-dimensional flow field without/with side fence were compared with experiment data and structure of three-dimensional flow filed.From the viewpoint of hypersonic vehicle airframe/propulsion integrated design,three-dimensional configuration of afterbody/nozzle was cons...
Keywords:hypersonic vehicle  integrated design  afterbody/nozzle  three-dimensional configuration  numerical simulation  
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