Numerical Simulation of the Effect of Engine Jet on the Base Flow of Vehicle

被引：0
|
作者：
Li G.-L. [1 ]
Yang Y.-J. [1 ]
Gong A.-L. [1 ]
Liu Z. [1 ]
机构：
[1] China Academy of Aerospace Aerodynamics, Beijing
来源：
| 2018年 / China Spaceflight Society卷 / 39期
关键词：
Cold jet method; Engine jet; Hot jet method; Nozzle;
D O I：
10.3873/j.issn.1000-1328.2018.01.012
中图分类号：
学科分类号：
摘要：
The study on the effect of engine jet on base flow is performed and the method for both cold and hot jet is proposed. Compared with the experiment data of high-pressure nozzle jet, the computational results agree with it and the set of method is proved. The vehicle in this paper is computed by cold and hot jet method and the results on monitoring spot are compared with the flight data. The difference in results by two methods is analyzed. The hot jet method is utilized for Mach number at 2.5. The different flight altitudes and total pressures of nozzle inlet are chosen to be computed for exploring the effect on jet diffusion and base flow. The results show that with the increase of total pressure, the pressure coefficients on base swing up and the highest of the mass fraction of fuel gas lies on base wall and keeps a relative constant, and with the increase of flight altitude, the high-speed zone in jet moves downward and the max Mach number increases. In addition, at certain flight altitude, the pressure coefficient on base has changed to be positive from being negative, which will affect range of vehicle and should be assessed ahead. © 2018, Editorial Dept. of JA. All right reserved.
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页码：89 / 96
页数：7
相关论文
共 12 条
  • [1] Xiao Z.-X., Fu S., Study on supersonic base flow using RANS/LES method, Chinese Journal of Computational Physics, 26, 2, pp. 221-230, (2009)
  • [2] Gao R.-Z., Yan C., LES/RANS hybird method for supersonic axisymmetric base flow, Journal of Beijing University of Aeronautics and Astronautics, 37, 9, pp. 1095-1099, (2011)
  • [3] Zhu D.-H., Shen Q., Numerical study of the stability of hypersonic base flow over a blunt body and Apollo command module, Chinese Journal of Theoretical and Applied Mechanics, 44, 3, pp. 465-472, (2012)
  • [4] Soshi K., Kozo F., Computational analysis of the characteristics of subsonic, transonic and supersonic base flows, The 35th AIAA Fluid Dynamics Conference and Exhibit, (2005)
  • [5] Pramod S., Graham V.C., Numerical investigation of supersonic base flows using DES, The 43rd Aerospace Science Meeting and Exhibit Conference, (2005)
  • [6] Francs S., Sebastein D., Philippe G., Et al., RANS-LES simulations of supersonic base flow, The 44th Aerospace Science Meeting and Exhibit Conference, (2006)
  • [7] Krishnendu S., Eeffect of Reynolds number on detached eddy simulation of hypersonic base flow, The 45th AIAA Aerospace Science Meeting and Exhibit Conference, (2007)
  • [8] Soo H.P., Sumanta A., An improved formulation of k-εturbulence models for supersonic base flow, The 17th AIAA Computational Fluid Dynamics Conference, (2005)
  • [9] Bannink W.J., Bakker E.M., Base flow/underexpanded exhaust plume interaction in a supersonic external flow, The 8th AIAA International Space Planes and Hypersonic Systems and Technology Conference, (1998)
  • [10] Bakker P.G., Bannink W.J., CFD validation for base flows with and without plume interaction, The 40th Aerospace Science Meeting and Exhibit Conference, (2002)
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