激波進氣道 的英文怎麼說

中文拼音 [jībōjìnqìdào]
激波進氣道 英文
shock intake
  • 激 : Ⅰ動詞1 （水因受到阻礙或震蕩而向上涌） swash; surge; dash 2 （冷水突然刺激身體使得病） fall ill fr...
  • 波 : Ⅰ名詞1 （波浪） wave 2 [物理學] （振動傳播的過程） wave 3 （意外變化） an unexpected turn of even...
  • 進 : 進構詞成分。
  • 氣 : Ⅰ名詞1 （氣體） gas 2 （空氣） air 3 （氣息） breath 4 （自然界冷熱陰晴等現象） weather 5 （氣味...
  • 道 : Ⅰ名詞（道路） road; way; route; path 2 （水流通過的途徑） channel; course 3 （方向; 方法; 道理） ...
  • 氣道 : air flue; air passage
  1. With account for the effect of temperature and shock - boundary layer interaction, the forebody / inlet with plane lip and wedge lip are designed by using the design methods of constant shock wave intensity and constant shock wave angle. in the design, the incidence angle of the first ramp, height of isolator, length of forebody and total turning angle of the designed forebody / inlet models are given

    另外，根據優選結果，給定前體長度、前體預壓縮楔角、總壓縮轉角及隔離段高度，分別用等激波強度和等激波角度的方法設計了唇口平直和唇口帶楔角的前體進氣道。
  2. 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。
  3. Complex wave structures of supersonic inlet at critical status are achieved by numerical simulation, and analysis on flow structure characteristic and shock wave structure is made

    得到了臨界工況下超聲速進氣道內外粘性流場復雜的波系結構，分析了流場結構特性和激波波系結構。
  4. The ram - compressed technology in ram - compressed rotor is the key of the rotating ramjet. we discussed it detailedly in some aspect such as theoretic analysis and numerical simulation and model test, and then point out that the essential of the ram - compressed technology is the air is compressed by the moving shock wave. the formula of parameter both sides the moving shock wave and

    指出了旋轉激波壓縮是旋轉沖壓壓縮的主要方式，推出了旋轉激波壓縮的參數關系式和沖壓轉子進氣道和盤腔中的簡化運動方程和壓力方程，並通過對冷態流場的數值模擬及模型試驗研究驗證了上述理論分析結果，為旋轉沖壓發動機沖壓轉子的設計分析奠定了理論基礎。
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