Volume 31 Issue 8
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SHI Xiao-juan, JI Hong-hu, SI Ren. Numerical investigation of geometric parameters' influence to aerodynamic performance of two dimensional convergent and divergent nozzle[J]. Journal of Aerospace Power, 2016, 31(8): 1799-1810. doi: 10.13224/j.cnki.jasp.2016.08.002
Citation: SHI Xiao-juan, JI Hong-hu, SI Ren. Numerical investigation of geometric parameters' influence to aerodynamic performance of two dimensional convergent and divergent nozzle[J]. Journal of Aerospace Power, 2016, 31(8): 1799-1810. doi: 10.13224/j.cnki.jasp.2016.08.002
shu

Numerical investigation of geometric parameters' influence to aerodynamic performance of two dimensional convergent and divergent nozzle

doi: 10.13224/j.cnki.jasp.2016.08.002

  • Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

  • Received Date: 2014-12-02
  • Publish Date: 2016-08-28
    Abstract
  • The computational cases were designed using the orthogonal experiment design method. The effect of eight geometric parameters on the aerodynamic performance of two dimensional convergent and divergent (2D-CD) nozzle was investigated. The geometric parameters studied include length to diameter ratio, cross-sectional area change rate, long half shaft rate, short half shaft rate of the super elliptic transition section, and throat width to height ratio, throat radius ratio, convergence half angle, divergent half angle of primary nozzle. The sensitivity analysis of throat aspect ratio, throat radius ratio, convergent half angle, divergent half angle on aerodynamic performance was performed. The results show that throat radius ratio is the main parameter of 2D-CD nozzle's aerodynamic performance, therefore the throat radius ratio should be increased in the 2D-CD nozzle design, especially when the convergent half angle is larger. Width to height ratio of throat is not a major parameter of 2D-CD nozzle's aerodynamic performance. The aerodynamic performance of 2D-CD nozzle is independent of transition duct.

     

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    • References(18)
  • [1]
    Capone F J.The nonaxisymmetric nozzle:it is for real[R].AIAA 79-1810,1979.
    [2]
    季鹤鸣,雷雨冰,邵万仁.二元收扩喷管的方案设计与试验研究[J].航空发动机,1995,21(4):8-13. JI Heming,LEI Yubing,SHAO Wanren.Concept design and experimental study of the 2D-CD nozzle[J].Aeroengine,1995,21(4):8-13.(in Chinese)
    [3]
    斯仁,吉洪湖,刘常春,等.冷却抑制二元收扩喷管红外特征的模型实验与数值研究[J].推进技术,2014,35(4):463-469. SI Ren,JI Honghu,LIU Changchun,et al.Model experiment and numerical analysis on infrared character and infrared suppression by cooling of two-dimensional convergent-divergent nozzle[J].Journal of Propulsion Technology,2014,35(4):463-469.(in Chinese)
    [4]
    Reichert B A,Hingst W R,Okiishi T H.An experimental trace gas investigation of fluid transport and mixing in a circular-to-rectangular transition duct[R].AIAA 91-2370,1991.
    [5]
    Davis D O.Experimental investigation of turbulent flow through a circular-to-rectangular transition duct[R].NASA TM 105210,1991.
    [6]
    Poinsatte P,Thurman D,Hippensteele S.Heat transfer in a superelliptic transition duct[R].NASA TP 214943,2008.
    [7]
    Wu C,Farokhi S,Taghavi R.A computational study of advanced exhaust system transition ducts with experimental validation[R].AIAA 92-3794,1992.
    [8]
    Burley J R,Carlson J R.Circular-to-rectangular transition ducts for high-aspect ratio nonaxisymmetric nozzles[R].AIAA 85-1346,1985.
    [9]
    Burley J R,Bangert L S,Carlson J R.Static investigation of circular-to-rectangular transition ducts for high-aspect-ratio nonaxisymmetric nozzles[R].NASA TP 2534,1986.
    [10]
    李娜.混合排气二元收敛喷管气动与红外隐身综合设计方法研究[D].南京:南京航空航天大学,2010. LI Na.Aerodynamic and infrared stealth comprehensive design of 2D convergent nozzle of mixed flow[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2010.(in Chinese)
    [11]
    Mason M L,Putnam L E,Bangert L S.The effect of throat contouring on two-dimensional converging-diverging nozzles at static conditions[R].NASA TP 1704,1980.
    [12]
    Berrier B L,Re R J.Effect of several geometric parameters on the static internal performance of three nonaxisymmetric nozzle concepts[R].NASA TP 1468,1979.
    [13]
    Bare E A,Reubush D E.Static internal performance of a two-dimensional convergent-divergent nozzle with thrust vectoring[R].NASA TP 2721,1987.
    [14]
    Milton L,Taylor J G,Frassinelli M C.Static internal performance of a two-dimensional convergent-divergent nozzle with external shelf[R].NASA TM 4719,1996.
    [15]
    Hamed A,Vogiatzis C.Overexpanded two-dimensional convergent-divergent nozzle performance,effects of three-dimensional flow interactions[J].Journal of Propulsion and Power,1998,14(2):234-240.
    [16]
    宁怀松,张志学,邵万仁,等.二元收扩喷管气动方案优化设计[J].航空发动机,2014,40(3):52-55. NING Huaisong,ZHANG Zhixue,SHAO Wanren,et.Internal performance optimization of 2D-CD nozzle[J].Aeroengine,2014,40(3):52-55.(in Chinese)
    [17]
    《航空发动机设计手册》总编委会.航空发动机设计手册:第7册进排气装置[M].北京:航空工业出版社,2000.
    [18]
    邱轶兵,张文利,闵凡飞,等.试验设计与数据处理[M].合肥:中国科学技术大学出版社,2008.
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