inlet compression ratio 中文意思是什麼

inlet compression ratio 解釋
進氣道增壓比
  • inlet : n. 1. 進口，入口。2. 【電學】引入，輸入，輸入線。3. 水灣，小港。4. 插入物，鑲嵌物。vt. （inlet, inletting）1. 引進。2. 嵌入，插入。
  • compression : n. 1. 壓縮；壓緊；濃縮，緊縮。2. 加壓；壓抑。3. （表現的）簡練。4. 應壓試驗。
  • ratio : n. （pl. ratios）1. 比，比率，比值；比例；系數。2. 【經濟學】復本位制中金銀的法定比價。vt. 1. 用比例方式表達；求出…的比值；使…成比例。2. 將（相片）按比例放大或縮小。
  1. The best compression ratio and fuel injection advance angle are calculated through mess optimization calculation program of language c. on the basis, optimization simulation of inlet and exhaust timing has been carried with the diesel engine working model to increase diesel engine ' s volumetric efficient

    在此基礎上，利用柴油機工作過程模型，對進排氣正時進行了優化計算，以提高柴油機的充氣效率，改善燃燒性能，為進一步改善該機性能指明了方向。
  2. Based on the variables of inlet length, compression ratio, inlet opening phase and the exhaust closing phase, multi - objective optimization was conducted for power, torque, combustion noise and fuel consumption indicators with constraint conditions of fuel consumption rate and the maximum breakout pressure

    以進氣道長度、壓縮比、進氣開啟相位、排氣關閉相位為可變因素；以比油耗、最高爆發壓力為約束條件，針對滿足功率、扭矩、燃燒噪聲和油耗指標進行多目標優化設計。
  3. A parametric analysis of the inviscid effects of leading edge sweep, sidewall compression, width - height ratio, cowl position and inflow mach number on spillage is finished. numerical simulations are completed for a series of inlets at various flight height and velocity. the research indicates that the area of spillage window, which is mainly determined by the position of the cowl, significantly influences the spillage characteristic of the scramjet inlet

    闡明了側板后掠的側壓進氣道設計參數對構型溢流影響;對不同側板配置方式的側壓式進氣道進行了數值模擬，通過對比分析，發現由唇口板的位置所決定的溢流窗面積的大小對進氣道溢流特性的影響顯著。
  4. In this thesis, hypersonic sidewall compression inlet ' s self - starting characteristics are numerical simulated and tested. with increasing mach number of inflow gradually, the hypersonic sidewall compression inlets can self - start. compared with the hypersonic sidewall compression inlet starting directly, characteristics are different. moving cowl, decreasing interior contraction ratio also can realize the hypersonic sidewall compression inlet ' s self - starting because of separation bubble on sidewall spilling out

    其次，在數值模擬結果的基礎上，設計了實驗模型和裝置並在馬赫3 . 85的風洞中進行了移動唇口板減小內收縮比實現側壓式進氣道自起動的風洞實驗，驗證了數值模擬的結果。
  5. It is no effect on a sidewall compression inlet ' s starting characteristics while a starting sidewall compression inlet is moved cowl to increase interior contraction ratio appropriately. back pressure effect on characteristics of self - starting for hypersonic sidewall compression inlet is tested in mach 3. 85 wind tunnel. the hypersonic sidewall compression inlet with interior contraction ratio 1. 24 can self - start. unstart hypersonic sidewall compression inlet caused by high back pressure can self - start by moving cowl to decrease interior contraction ratio

    最後，實驗研究了反壓對側壓式進氣道自起動特性的影響，內收縮比1 . 24的側壓式進氣道可以實現自起動並且實驗驗證了由於反壓過高而不起動的側壓式進氣道，通過移動唇口板以減小內收縮比可以實現側壓式進氣道的自起動。
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