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ACTA AERONAUTICAET ASTRONAUTICA SINICA ›› 1990, Vol. 11 ›› Issue (8): 396-399.

• 论文 • Previous Articles     Next Articles

FLOWFIELD COMPUTATION OF 2-C-D NOZZLE

Chen Baisong1, Wu Da2   

  1. 1. The 2nd Aerotechnology School of Air Force;2. Beijing University of Aeronautics and Astronautics
  • Received:1989-01-30 Revised:1989-04-05 Online:1990-08-25 Published:1990-08-25

Abstract: The flowfield equations of 2-C- D nozzle have been solved by a time-dependent finite difference method known as two step MacCormack technique. The computational results of nozzle wall pressure distribution and thrust agree with experimental data well. A complicated shock system have been attained through the computation of exhaust flow-field.

Key words: plume, exhaust jet, computational fluid dynamics