Numerical Study and Performance Prediction for Gaseous Hydrogen/Oxygen Bell Nozzle

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  • TSUBOI Nobuyuki
    Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency
  • ITO Takashi
    Institute of Aerospace Technology, Japan Aerospace Exploration Agency
  • MIYAJIMA Hiroshi
    Institute of Aerospace Technology, Japan Aerospace Exploration Agency

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Three-dimensional reactive full Navier-Stokes simulations of hydrogen/oxygen flow in a nozzle with area ratio of 140 are evaluated using a detailed chemical kinetics reaction model. The flows over each overlapped grid are computed using a unified zonal method technique. The flow field computed by the present CFD code shows good agreement with the flow field computed by the TDK code except the position of the weak compression wave focusing on the nozzle axis. Isp profiles of the subscale nozzle computed by the CFD code assuming a laminar condition agree well with the experiment and those calculated by the TDK code. The measured heat flux distributions at higher nozzle expansion ratios also agree well with the laminar CFD results. The inconsistency of the prediction of turbulent boundary layer loss between TDK and CFD leads to some difference in Isp. The effect of grid resolution on Isp turned out to be small in the present conditions.

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