本文係利用數值方法模擬突張管超音速 燃燒流場。數值方法採用MacCormack 1969年 提出之顯式法解非穩態、可壓縮、黏性的 Navier-Stokes方程式。文中紊流模式係採用 雙層紊流模式,此模式為一簡單的代數式,無須 找尋邊界層緣。燃燒模式則採用H/sub 2/-air完 全燃燒反應模式。首先計算超音速突張冷流場,並 與現有文獻現象相比較,可發現計算結果與實驗照片相吻合,證明本數值方法之正確性。其 次計算注入流加入氣態氫燃料,在不同壓力時 的冷流場燃料分布情形。最後再計算分析在不 同壓力時的燃燒流場探討壓力的改變對整個熱 流場的影響。本文可建立對高速燃燒室內流場 的瞭解與基本計算能力,以期進一步的應用於 超音速衝壓引擎。 The present paper employed the MacCormack fully implicit scheme (1981) to solve unsteady, compressible, and viscous Navier-Stokes equation. The H/sub 2/-air complete combustion model was used to calculate combustion field. The turbulent viscosity was determined from two-layer model. The supersonic sudden expansion laminar flow was calculatd to make sure that the program was workable. The turbulent flow was calculated and the results were compared with experimental data to make sure that turbulent model employed was qualitatively correct. The shock wave propagation in supersonic internal flow were studied and the effects of inlet on both cold and hot flow fields were also investigated.
關聯:
中國航空太空學會民國七十九年學術研討會論文集=The Aeronautical and Astronautical Societyof the Republic of China，頁1013-1024
