nozzle exit中文是什么意思

發(fā)音:

中文翻譯
造句

噴管出口
噴口截面
噴嘴出口
噴嘴口

nozzle n. 管嘴；噴嘴；〔俚語〕鼻子。 a jet [prop ...
exit vi. 〔拉丁語〕【戲劇】退場(chǎng) 〔cf. exeunt ...
exit nozzle 出口噴管; 排氣噴管
exit area of nozzle 噴嘴出口面積
exit nozzle throat 噴管喉道; 噴管臨界截面; 噴嘴臨界截面
exit-nozzle geometry 排氣噴管幾何形狀
fixed exit nozzle 定出口截面噴管
fixed-exit nozzle 固定出口噴管
non expanding exit nozzle 圓桶形排氣管
non-expanding exit nozzle 圓桶形排氣管
nozzle exit angle 噴管出口角
nozzle exit area 導(dǎo)管出口面積; 噴管出口面積; 噴口面積
nozzle exit conditions 噴管出口條件
nozzle exit diameter 噴管出口直徑
nozzle exit mach number 噴管出口馬赫數(shù)
nozzle exit momentum 噴出動(dòng)量; 噴管出口動(dòng)量
nozzle exit plane 噴管出口面
nozzle exit pressure 噴管出口壓力; 噴管壓力; 噴嘴壓力
nozzle exit section 噴管出口截面
turbine nozzle exit velocity 渦累導(dǎo)向器氣體流出速度; 渦輪導(dǎo)向器氣體流出速度
uniform exit flow nozzle 均勻出口氣流噴管
exit n. 1.出口，出路，太平門。 2.【電學(xué)】引出端；排氣管。 3.外出；離去；死亡；【戲劇】退場(chǎng)(opp. entrance)。 make one's exit退出；退場(chǎng)；去世。 vi. 1.退出，離去。 2.死，去世。 vi. 〔拉丁語〕【戲劇】退場(chǎng) 〔cf. exeunt; opp. enter〕.
no exit 此門不通; 毫無出路; 禁止通行; 沒有出口; 無路可出
nozzle n. 管嘴；噴嘴；〔俚語〕鼻子。 a jet [propelling] nozzle 【火箭】尾噴管。
abend exit 異常終止出口

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例句與用法

Preform technology of carbon - carbon composites nozzle exit cone
炭材料出口錐預(yù)制體技術(shù)
Effects of preform structure on mechanical properties of carbon - carbon composite for nozzle exit cone
噴管出口錐材料力學(xué)性能的影響
Uniform distribution of cavitation at the nozzle exit section is obtained by increasing length - diameter ratio and leads to the improvement of atomization
從燃油空穴霧化理論的角度出發(fā)，空穴強(qiáng)度的提高以及在出口截面上的均勻分布都有利于燃油的破碎霧化。
The experimental results show that the location of the diffuser should be close to the nozzle exit , and the shape and size of the diffuser entrance should match the nozzle exit
實(shí)驗(yàn)表明，擴(kuò)壓段應(yīng)安裝在距主噴管較近的位置，并具有與主噴管相匹配的入口面積和形狀。
The conclusion that the optimal secondary nozzle exit area generating the maximum thrust agrees well with the numerical simulation , indicating that the exit area of secondary nozzle should be optimized according to structure and flow parameters during design
表明在引射火箭設(shè)計(jì)時(shí)，應(yīng)結(jié)合引射火箭的結(jié)構(gòu)和流動(dòng)參數(shù)對(duì)二次噴管出口面積進(jìn)行優(yōu)化設(shè)計(jì)，以達(dá)到最佳推力性能。
The energy equation of the thrust chamber wall was developed by omitting radical heat conduction and only considering the radiation heat transfer of the four chambers , the radiation leakage through nozzle exit , the axial and circular heat conduction
忽略徑向?qū)幔紤]推力室外向的相互及自身輻射交換、內(nèi)壁經(jīng)噴口的輻射泄漏以及周向和軸向的傳導(dǎo)熱量，建立了推力室壁的能量方程。
The ratio of mach number between lateral jet and free flow induce intensity degree of jet interaction . it has no obvious difference between two interactions with two types of nozzle exit configuration , rectangle and ellipse . the shock in front of jet results in increase of shock resistance and the jet ejection causes increase of base resistance
研究表明，側(cè)噴流與來流馬赫數(shù)之比是影響繞流場(chǎng)的重要因素，該值越大則側(cè)噴干擾越強(qiáng)烈，矩形和橢圓形兩種側(cè)噴口形狀對(duì)側(cè)噴流場(chǎng)干擾波系的影響并不明顯。
Abstract : optimum distances between primary nozzle exit and mixing tube inlet , static pressure recovery of the mixing flow in mixing tube 、 total pressure distributions at the exit of mixing tube 、 pumping coefficients and total pressure losses of the exhaust ejector systems with four different types of primary nozzles have been measured in the experiments
文摘:對(duì)4種主噴管組成的排氣引射系統(tǒng)的引射系數(shù)和總壓損失、各主噴管出口與混合管進(jìn)口之間的最佳間距、混合氣流在混合管內(nèi)的靜壓恢復(fù)及混合氣流在混合管出口處的總壓分布等進(jìn)行了測(cè)量和對(duì)比。

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