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[1]汪昆,谢旅荣,刘雨.二维超声速进气道扩张段性能计算[J].火箭推进,2017,43(06):54-60.
　WANG Kun,XIE Lrong,LIU Yu.Performance calculation of two-dimensional supersonic inlet diffuser[J].Journal of Rocket Propulsion,2017,43(06):54-60.
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二维超声速进气道扩张段性能计算

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 43 期数: 2017年06期 页码: 54-60 栏目: 研究与设计 出版日期: 2017-12-30
Title:
Performance calculation of two-dimensional supersonic inlet diffuser
文章编号:
1672-9374(2017)06-0054-07
作者:
汪昆1; 2; 谢旅荣1; 2; 刘雨1; 2
1.南京航空航天大学 能源与动力学院,江苏 南京 210016; 2.江苏省航空动力系统重点实验室,江苏 南京 210016
Author(s):
WANG Kun1; 2;  XIE Lürong1; 2;  LIU Yu1; 2
1.College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China; 2.Jiangsu Province Key Laboratory of Aerospace Power System, Nanjing 210016, China
关键词:
超声速进气道;  进气道扩张段;  中心线变化规律;  扩张比;  中心线偏距
Keywords:
supersonic inlet;  inlet diffuser;  law of centerline variation;  expansion ratio;  centerline offset
分类号:
V431-34
文献标志码:
A
摘要:
研究了一种二维超声速进气道扩张段型面的中心线变化规律、扩张比及中心线偏距对设计状态下进气道的气动性能及流场的影响。结果表明:采用前缓后急中心线变化规律的进气道出口总压恢复系数最高,而采用前急后缓中心线变化规律的进气道总压恢复系数最低; 随着扩张比从1.40增大到1.80,进气道总压恢复系数和抗反压能力均下降,出口马赫数上升, 扩张比与长度对进气道出口参数的影响存在较强的耦合关系; 随着偏距比的增加,进气道总压恢复系数起初有一定的升高,但偏距比增大到0.80之后,总压恢复系数降低,出口马赫数增大,总体上偏距比变化对进气道抗反压能力影响不大。
Abstract:
The influences of the law of centerline variation, expansion ratio and centerline offset of two-dimensional supersonic inlet diffuser on aerodynamic performance and flow characteristics under inlet design condition are studied. The numerical results indicate that the inlet with diffuser rapid turning at its exit has maximum total pressure recovery coefficient and inlet with diffuser rapid turning at the entrance has minimum total pressure recovery coefficient; as the expansion ratio increases from 1.40 to 1.80, inlet total pressure recovery coefficient and backpressure-resistance ability decrease, and the exit Mach number increase; the effect of expansion ratio and length on inlet exit parameter has a strong coupling relationship. As offset ratio increases, the inlet total pressure recovery coefficient increases at the beginning, but as the offset ratio increases to more than 0.80, the inlet total pressure recovery coefficient declines and the exit Mach number increases. General speaking, the variation of offset ratio has little effect on backpressure-resistance ability of the inlet.

参考文献/References:

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备注/Memo

收稿日期:2017-03-22
作者简介: 汪 昆(1993—),男,硕士研究生,研究领域为内流气体动力学

更新日期/Last Update: 1900-01-01