出口面积的英文

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"出口面积"怎么读用"出口面积"造句

英文翻译手机版

discharge area
exit area
outlet area

"出口"英文翻译 exit
"面积"英文翻译 area
"排出口面积" 英文翻译 : exhaust port area
"导管出口面积" 英文翻译 : nozzle exit area
"排气出口面积" 英文翻译 : exhaust exit area
"喷管出口面积" 英文翻译 : exhaust jet area; nozzle exit area
"喷嘴出口面积" 英文翻译 : exit area of nozzle; outlet area of nozzle
"解租地区出口面积" 英文翻译 : discharge area
"喷射气流出口面积" 英文翻译 : exhaust jet exit area
"出口面" 英文翻译 : exit face
"瓣口面积" 英文翻译 : valve orifice area
"舱口面积" 英文翻译 : hatch area
"断口面积" 英文翻译 : area of fracture; fracture area
"喉口面积" 英文翻译 : throat area
"节流口面积" 英文翻译 : choke area
"进风口面积" 英文翻译 : air-admitting surface
"进口面积" 英文翻译 : entry area; exit area; inlet area; inlet-duct area; intake area
"开口面积" 英文翻译 : aperture area; opening area; port area; port-area
"开口面积比" 英文翻译 : open area ratio
"孔口面积" 英文翻译 : orifice area
"口面积计算" 英文翻译 : calculation of orifice area
"炉口面积" 英文翻译 : nose area
"排气口面积" 英文翻译 : discharge area
"排水口面积" 英文翻译 : freeing port area
"排泄口面积" 英文翻译 : draining area

例句与用法

Impeller diameters and outlet areas for industrial centrifugal fans
工业离心式风扇的叶轮直径和出口面积
The influence of the area contraction ratio of rotary flow generator on the hydraulic characteristics of level rotary flow has been investigated by the hydraulic model test of an internal energy dissipation tunnel
摘要通过模型试验，研究了起旋器出口面积收缩率对水平旋流泄洪洞水力特性的影响。
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
表明在引射火箭设计时，应结合引射火箭的结构和流动参数对二次喷管出口面积进行优化设计，以达到最佳推力性能。
The results indicate that with decrease of exit area of secondary nozzle , the bypass ratio is decreasing , and the static pressure in integrated ejector combustor is increasing , and mixing condition becomes better . there exists an optimal exit area of secondary nozzle to get maximum thrust of rocket ejector
结果表明：引射能力随着二次喷管出口面积的减小而减小；整体式引射燃烧室压强随着二次喷管出口面积的减小而上升，混合随之更为充分；存在一个最优的二次喷管出口面积，使发动机推力最大。
It is shown that when the exit area of secondary nozzle and the fuel / oxidizer ratio is fixed , the increase of mass flow rate of secondary flow lead to the decrease of velocity of mixed flow , and increase of total mass flow rate . the synthetical result of these two phenomenon cause the increase of thrust of rocket ejector , but the increasing magnitude is relatively small , indicating that these is no necessary to claim large bypass ratio in rocket ejector design . in the comparison between two configurations , the typical one has better performance , indicating the importance of pressure ratio
结果表明：在固定二次喷管出口面积和氧燃比的条件下，二次流(引射空气流)流量的增加引起混合气体出口速度的下降和总流量的增加，二者综合作用使发动机推力增加，但增幅不大，表明在设计发动机结构和工作参数时，不必过分追求大的引射系数；两种结构的性能对比分析表明了增压比对引射火箭性能的提高具有重要意义；对引射火箭的热力循环分析同样表明，增压比对于提高发动机性能非常关键。
The effect of secondary fuel nozzle location , the mass flow rate of secondary fuel and outlet area of ejectorjet were studied . the main results are : the geometry structure of ejectorjet can be compatible with other rbcc operation modes by secondary combustion organization ; the distribution of secondary fuel on ejectorjet cross section is significant for secondary combustion stability . spi combustion organization method is promising
实验研究了二次燃料喷注位置、二次燃料喷注量、后体出口面积对引射火箭性能的影响，得到的结论为：通过燃烧组织，引射火箭模态可以和其他工作模态(亚燃超燃)共用燃烧室而不需做大的几何变化；二次燃料在引射火箭通道截面上的分布对于引射火箭的稳定工作有重要意义。
The experimental results indicates that the secondary mass flow increases with increasing of primary mass flow rate , but the bypass decrease because the primary mass flow rate increase more rapidly than secondary mass flow . the expansion configuration shows low thrust property due to low pressure in flow path . the secondary nozzle changes the pressure distribution in ejector combustor , and decreases bypass ratio , but obtain more completely mixing
结果表明：二次流流量随着一次流流量的增加而增加，由于二次流流量的增加速度低于一次流，引射系数减小；在纯扩张式结构实验中，引射燃烧室压强很低，难以实验推力增强；二次喷管改变了引射燃烧室的压强分布，降低了引射系数，改善了混合状况能；对于本文的实验结构，存在一个最优的二次喷管出口面积，使引射火箭推力最大，同数值模拟结果相吻合。