Numerical analysis of bipropellant combustion in orbit maneuvering vehicle thrust chamber

H. H. Chiu, T. L. Jiang, A. N. Krebsback, K. W. Gross

Research output: Contribution to conferencePaperpeer-review

1 Citation (Scopus)


The combustion and aerodynamic processes of liquid-liquid bipropellant; monomethylhydrazine and nitrogen tetroxide in the combustion chamber of a variable thrust engine (VTE) have been examined to assess the flow structure, combustion characteristics, and wall heat transfer under the simulated engine operations at two power levels. The Generalized Elliptic Multi-phase flow with Chemical reaction, Heat transfer and Interfacial Processes (GEM-CHIP) code and the Bipropellant Combustion (BICOMB) code, which is the GEMCHIP algorithm reformulated in the frame work of a body fitted coordinate system, have been used for the numerical study. Combustion flow structure with non-premixed type injection that simulates the impingement type injector is predicted and the results are compared with that of the premixed injector.

Original languageEnglish
Publication statusPublished - 1990
Event28th Aerospace Sciences Meeting, 1990 - Reno, United States
Duration: 1990 Jan 81990 Jan 11


Other28th Aerospace Sciences Meeting, 1990
Country/TerritoryUnited States

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering


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