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題 名 | 極音速進氣道設計與風洞測試=Hypersonic Inlet Design and Wind Tunnel Test |
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作 者 | 周大偉; 賴祐炫; 吳有傳; | 書刊名 | 新新科技年刊 |
卷 期 | 11 2015.01[民104.01] |
頁 次 | 頁48-59 |
分類號 | 447.553 |
關鍵詞 | 超燃衝壓引擎; 極音速進氣道; 數值模擬; 風洞測試; Scramjet; Hypersonic inlet; CFD; Wind tunnel testing; |
語 文 | 中文(Chinese) |
中文摘要 | 超燃衝壓引擎是現今最適合於極音速領域續航之吸氣式推進系統,超燃衝壓引擎主要由進氣道、隔離段、燃燒室及噴嘴尾管所組成,極音速進氣道為超燃衝壓引擎之重要組件,其與飛行載具之彈前體是合為一體,極音速進氣道提供燃燒室所需之空氣流量,同時對進氣空氣進行減速增壓,以滿足超音速燃燒之需求。本研究將透過一個案例來說明極音速進氣道設計時須著重的議題,採用數值模擬來輔助進氣道外形之設計與分析,最後再透過氣道風洞模型測試完成進氣道性能驗證。 |
英文摘要 | Scramjet engine is one of the most efficient air-breathing engines for hypersonic cruise. It is usually formed by the hypersonic inlet, isolator, combustor, and nozzle. The design of hypersonic inlet is a key of scramjet engine performances. Because of the nature of hypersonic flow, the concept of hypersonic inlet design is quite different from the supersonic inlet that used in a ramjet. This paper discusses some differences between the supersonic and the hypersonic inlet by a design example. The hypersonic inlet design was initially achieved by using the experience of supersonic inlet. The 2D CFD analysis was performed to determine the effects of shock/boundary-layer interaction and to tune the design parameters. The performances of the modified hypersonic inlet were then verified by wind tunnel tests. |
本系統中英文摘要資訊取自各篇刊載內容。