## 摘要

A mathematical model for computation of turbulent reacting flows is developed under general curvilinear coordinate systems. An adaptive, streamline grid system is generated to deal with the complex flow structures in a multiple-inlet solid-propellant ducted rocket (SDR) combustor. General tensor representations of the k-t and algebraic stress (ASM) turbulence models are derived in terms of contravariant velocity components, and modification caused by the effects of compressible turbulence is also included in the modeling. The clipped Gaussian probability density function is incorporated in the combustion model to account for fluctuations of properties. Validation of the above modeling is first examined by studying mixing and reacting characteristics in a confined coaxial-jet problem. This is followed by study of nonreacting and reacting SDR combustor flows. The results show that Gibson and Launder’s ASM incorporated with Sarkar’s modification for compressible turbulence effects based on the general curvilinear coordinate systems yields the most satisfactory prediction for this complicated SDR flowfield.

原文 | English |
---|---|

頁（從 - 到） | 473-482 |

頁數 | 10 |

期刊 | Journal of Propulsion and Power |

卷 | 11 |

發行號 | 3 |

DOIs | |

出版狀態 | Published - 1995 |

## All Science Journal Classification (ASJC) codes

- 航空工程
- 燃料技術
- 機械工業
- 空間與行星科學