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

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  • Tsuboi Nobuyuki
    宇宙航空研究開発機構宇宙科学研究本部宇宙輸送工学研究系
  • Ito Takashi
    宇宙航空研究開発機構総合技術研究本部ロケットエンジン技術センター
  • Miyajima Hiroshi
    宇宙航空研究開発機構総合技術研究本部ロケットエンジン技術センター

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  • 酸水素反応を伴うベル型ノズルの数値解析および性能評価
  • サン スイソ ハンノウ オ トモナウ ベルガタ ノズル ノ スウチ カイセキ オヨビ セイノウ ヒョウカ

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Abstract

Three-dimensional reactive full Navier-Stokes simulations of hydrogen/oxygen flow in a nozzle having area ratio of 140 is evaluated using a detailed chemical kinetics reaction model. The flow over each overlapped grids is 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 distributes 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 on Isp. The effect of grid resolution turned out to be small on Isp in the present conditions.

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