Volume 23 Issue 6
Jun.  2008
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Article Navigation >  Journal of Aerospace Power  > 2008  >  23(6): 1146-1150
TIAN Hui, CAI Guo-biao, SUN Zai-yong. Computation of nozzle two-phase flow in a N2O/HTPB hybrid rocket motor[J]. Journal of Aerospace Power, 2008, 23(6): 1146-1150.
Citation: TIAN Hui, CAI Guo-biao, SUN Zai-yong. Computation of nozzle two-phase flow in a N2O/HTPB hybrid rocket motor[J]. Journal of Aerospace Power, 2008, 23(6): 1146-1150.
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Computation of nozzle two-phase flow in a N2O/HTPB hybrid rocket motor

  • 1.

    School of Astronautlcs, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

  • 2.

    The 41st Research Institute, The 6th Academy of China Aerospace Science and Industry Corporation, Hohhot 010010, China

  • Received Date: 2007-11-22
  • Rev Recd Date: 2008-04-11
  • Publish Date: 2008-06-28
    Abstract
  • Numerical solutions of full Navier-Stokes equations were obtained for a nozzle two-phase flow of the nitrous oxide(N2O)/hydroxyl-terminated polybutadiene(HTPB) based fuels hybrid rocket motor.MacCormack decomposition scheme and B-Lalgebraic turbulence model and two-phase equilibrium flow model were used.The nozzle flow and performance under three oxidizer-to-fuel ratios and four nozzle types were calculated.Effect of oxidizer-to-fuel ratio and nozzle type on nozzle performance was analyzed from the two-phase and gas phase results.Vacuum specific impulse is bound up with oxidizer-to-fuel ratio.This paper will be useful for the hybrid rocket motor design.

     

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    • References(6)
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