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[1]汪明生,杨建军.几何参数对逆流矢量喷管性能的影响研究[J].火箭推进,2009,35(02):30-36.
　Wang Mingsheng,Yang Jianjun.Effect of geometric performance of counterflow parameters on thrust vectoring nozzle[J].Journal of Rocket Propulsion,2009,35(02):30-36.
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几何参数对逆流矢量喷管性能的影响研究

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 35 期数: 2009年02期 页码: 30-36 栏目: 研究与设计 出版日期: 2009-04-30
Title:
Effect of geometric performance of counterflow parameters on thrust vectoring nozzle
作者:
汪明生; 杨建军
南京航空航天大学能源动力学院，江苏南京210016
Author(s):
Wang Mingsheng; Yang Jianjun
College of Energy and Power Engineering，Naming University of Aeronautics and Astronautics， Nanjing 210016，China
关键词:
逆流推力矢量; 数值模拟; 几何参数; 气动性能; 主流附体
Keywords:
counterflow vectoring thrust; numerical simulation; geometric parameters; pneuma—- tic performance; main flow attachment
分类号:
V434
文献标志码:
A
摘要:
采用数值模拟研究了逆流矢量喷管中主要几何参数(二=．次流道高度G与外套管 轴向长度￡、横向高度C、出口边缘斜切角研对气动性能的影响。结果表明，L或C的增加 均提高了矢量角，减少了合成推力系数，但较小的G(如0．2)更容易发生主流附体。当C=H (主喷管出12高度)时气动性能达到最佳，所对应的矢量角最大。口对气动性能的影响较小， 但对矢量角的最大值起到限制作用。
Abstract:
The effect of main geometric parameters(height of secondary flow path G，collar's axial length L horizontal height C，and inclining angle 0 at the exit)on the internal performance of a counterflow vectoring thrust nozzle was studied by numerical simulation．The results show that the vectoring angle increases with the rise of L and G(≥0．35)，while synthesis thrust coefficient re— duces．But the smaller G(such as 0．2)leads to main flow attachment more easily．There is an optimal value of the internal performance while C=H(exit height of main nozzle)，which is corresponding to a maximum vectoring angle．0 has less influence on the internal performance of the nozzle， however it can restrict the nlaximum vectoring angle．

参考文献/References:

[l]Hamed A,Laskowski G A,Parametric Study ofSlot Injection Thrust Vectoring in a 2DCD Nozzle[R]．AIAA 97-3154．
[2]Yagle P J，Miller D N，Ginn K B，et a1．Demonstration of Fluidic Throat Skewing for Thrust Vectoring in Structurally Fixed Nozzles[R]．2000-GT-0013。May 8-1 l， 2000．
[3]Deere K A，Berrier B L．Flamm J D．A Computational Study of a New Dual Throat Fluidic Thrust Vectoring Nozzle Concept[R]．AIAA 2005-3502．
[4]4 Strykowski PJ，Krothapalli A．111e Countercurrent Mixing Layer：．Strategies for Shear-layer Control[R]．AIAA93- 3260．
[5]Strykowski P J，Krothapalli A，Forliti D J．Counterflow Thrust Vectoring of Supersonic Jets[R]．AIAA96-01 15．
[6] Flamm,J D．Experimental Study of a Nozzle Using Fluidic Counterflow for Thrust Vectoring[R]．AIAA98-3255．
[7]杨建军．逆流控制的推力矢量喷管气动特性研究[D]．南 京：南京航空航天大学，2007．

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备注/Memo

收稿日期：2008—11-20；修回日期：2009-01-05。 作者简介：汪明生(1965一)，男，博士，研究领域为内流空气动力学与推进技术。

更新日期/Last Update: 1900-01-01