進口馬赫數 的英文怎麼說

中文拼音 [jìnkǒumǎhèshǔ]
進口馬赫數 英文
inflow mach number
  • 進 : 進構詞成分。
  • 口 : Ⅰ名詞1 （人或動物進飲食的器官; 嘴） mouth 2 （容器通外面的地方） mouth; rim 3 （出入通過的地方） ...
  • 馬 : Ⅰ名詞1 [動物學] （哺乳動物） horse 2 （象棋棋子） horse one of the pieces in chinese chess3 （姓...
  • 赫 : Ⅰ形1 （顯著; 盛大） conspicuous; grand 2 （紅如火燒） bright flaming redⅡ名詞1 [電學] （頻率單位...
  • 數 : 數副詞（屢次） frequently; repeatedly
  • 進口 : 1 （船隻進港） enter port; sail into a port2 （外貿進口） import3 （入口） entrance; [機械工程] i...
  1. The calculation results indicate that the starting performance of forebody / inlet with wedge - shaped lip is better than that with plane lip at low flight mach number. at high flight mach number, the performance of the forebody / inlets designed by the two methods is approximate. at low flight mach number, the starting performance of forebody / inlet designed by the method of constant shock wave intensity is better

    結果表明：唇口帶楔角的進氣道在低飛行馬赫數下的起動性能優于唇口平直的進氣道；採用等激波強度和等激波角度方法設計的進氣道在高飛行馬赫數下的性能相近，在低飛行馬赫數下，採用等激波強度方法設計的進氣道起動性能較優。
  2. In this dissertation, the pulse jet style, the influence on the shock wave, the flow in the tube and the cooling effect was deeply studied theoretically and experimentally. the influence of the pulse jet style on the forming of shock wave and the shock wave intensity was explored. the initial disconnection style in oscillating tube vented and the initial disconnection breakdown was proposed by different pulse jet style

    本文對脈動射流的型式及其對激波、管內流動及冷效應的影響進行了較系統的理論和實驗研究，主要包括:探討了脈動射流的型式對形成管內激波形成及激波強度的影響，給出了不同脈動射流的型式下振蕩管開口端初始間斷的類型，對初始間斷進行了分解，導出了包含進氣、排氣參數及工質物性參數的管內入射激波馬赫數mj的表達式，給出了管內激波形成的三種原因及其所對應的脈動射流型式和具體的工作狀態。
  3. The results prove that : ( 1 ) when the mach number of the flow at the exit increases, the total pressure recovery decreases, and the circular steady total pressure distortion coefficient, turbulence intensity and synthesis distortion increase

    研究結果表明： （ 1 ）地面工作狀態下，隨著出口馬赫數的增加，蛇形進氣道出口截面的總壓恢復系數不斷下降，而穩態周向畸變指數、紊流度和綜合畸變指數均上升，穩態徑向畸變指數變化不大。
  4. On basis of the modeling results, the effects of mach number, attack angle and ramp angle on the inlet performance are analyzed

    根據此數學模型，分析了攻角和進口氣流馬赫數對進氣道性能的影響，同時給出了斜板對進氣道性能的影響。
  5. To prove the accuracy of the mach number, and the parameter homogeneity of the design nozzle " s exit, cfd calculate has carried on the design results. under the condition of supersonic and hypersonic flow, and a certain range of temperature, and mach number, the conclusion of the influence of specific heat to nozzle design is drawn

    為了驗證所設計的噴管出口馬赫數的大小和噴管出口流場的均勻性，採用nnd格式和b l湍流模型求解雷諾平均n - s方程，對設計結果進行了cfd驗算，得出了在一定溫度范圍內，超音速、高超聲速流動的條件下，不同馬赫數范圍內變比熱容對噴管型面和噴管出口馬赫數的影響。
  6. 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。
  7. When the serpentine inlet is running at the exit mach number ma ( subscript e ) = 0. 45, the total pressure recovery coefficient equals 0. 90, and synthesis distortion equals 13. 85 %

    本研究的蛇形進氣道在出口馬赫數為0 . 45時，總壓恢復系數為0 . 90 ，綜合畸變指數為13 . 85 % ，總壓恢復較低，畸變較大，超出了一般航空發動機的承受范圍。
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