進氣道特性 的英文怎麼說

中文拼音 [jìnqìdàotèxìng]
進氣道特性 英文
inlet characteristics
  • 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） ...
  • 特 : Ⅰ形容詞（特殊; 超出一般） particular; special; exceptional; unusual Ⅱ副詞1 （特別） especially; v...
  • 性 : Ⅰ名詞1 （性格） nature; character; disposition 2 （性能; 性質） property; quality 3 （性別） sex ...
  • 氣道 : air flue; air passage
  • 特性 : characteristic（s）; character; performance; features; properties; behaviour; response; character...
  1. Design and performance of s - shaped inlet for high subsonic missiles

    彎進氣道設計及其特性
  2. The research object of this thesis is a chip - array that is fixed on one of printed circuit boards ( pcb ), which are located in a forced air field ( forced convection ) in an electronic case ; and from the essential equations of airflow we can deduce the mathematical model of the turbulent flow ; then we can establish the finite element algorithm and apply the fe software to work out the equations of turbulent flow, finally we can use the software to display and analyse the field of flow and temperature

    本文以處于強迫空氣對流流場中的某pcb板及其板上的電子元件陣列作為研究對象，推導了紊流流場的數學模型，並建立了相應的有限元求解格式，應用有限元法分析軟體對該系統的紊流流場和溫度場進行了模擬分析：解算出pcb板上各電子元件的溫度分佈；並提出了用於求解系統風道特性曲線的cfd方法。
  3. Reynolds numbers ( based on average velocity at passage inlet and hydraulic diameter of the passage ) are changing from 20000 to 80000 and the extraction ratios ( suction ratios, sr ) are changing from 0. 30 to 0. 60 for each test model. so the influences of reynolds numbers, suction ratios and etc. on the discharge coefficients and pressure loss characterist ics are also presented. flow fields of typical passages are visualized with the flow visualization techniques and measured with hot - wire anemometer

    對每一種通道結構，實驗在不同通道進口雷諾數（ re = 20000 、 40000 、 60000 、 80000 ）和不同通道總出流比（ sr = 0 . 30 、 0 . 45 、 0 . 60 ）下進行，以研究這兩個流動參數及其它相應變化的參數（氣膜孔的雷諾數re _ h 、氣膜孔與通道的動量比i等）對出流特性和流阻特性的影響規律。
  4. According to the measuremental data of the two ammunications, the anti - designed computation and analysis of aerodynamic characteristic, flight stability, exterior ballistic characteristic for the two ammunications are studied with the advanced methods of the exterior ballistics. using the monte calo algorithm, the statistic mathematical model about ammunication ' s intensity is established and the 1000 miter vertical target intensity and the fall intensity are discussed in detail for the two ammunications. the improval potential and the main technical approachs of these ammunication ' s exterior ballistic performances are presented by compositive optimal algorithm

    根據工廠對俄ak130艦炮彈藥的測繪數據，利用先進的外彈道數值分析方法對兩種彈藥的空氣動力特性、飛行穩定性特性、外彈道特徵量等進行了反設計計算分析；採用montecarlo方法，建立了艦炮彈藥密集度性能統計分析數學模型，對兩種彈藥的立靶密集度和地面密集度進行了詳細的計算分析；利用外彈道性能綜合優化設計方法對兩種彈藥的外彈道性能指標的改進潛力和主要技術途徑進行了分析。
  5. By this means, the performance of the shock absorber is improved as well as the quality of suspension system. after tested on the testing equipment and on the road condition matched with the car, outer performance of the double - tube gas hydraulic shock absorber pr ove to be excellent and the indicator diagram are full and smooth. the operation and control of vehicle are also obviously improved. with the improvement of domestic components as well as gas charging equipment and gas charging workmanship, the double - tube hydraulic shock absorber meets domestic market requirements and will have a better prospect

    我們對研製的雙筒充氣液壓減振器進行了臺架試驗和裝車道路試驗，表明這種減振器具有優良的外特性，其示功圖豐滿、圓滑，車輛操縱性明顯改善。隨著我國零部件質量水平的提高，及充氣設備、充氣工藝的改進，雙筒充氣液壓減振器將有更廣闊的發展空間，適合我國的國情。
  6. Sum up, the study of intake port is significant for the design of intake port and the development of engine. at present, the study of flow characters in intake port of engine mainly depends on experiment. numerical simulation is not universal, especially for the engine with dual - intake port

    目前，國內對發動機進氣道的流動特性研究手段主要依靠實驗，在實驗臺上進行大量的實驗，既費時又費力，實驗方法顯得過于陳舊過時，已不能適應現代高性能發動機研製工作的需要，因此，採用多維數值模擬技術是一種有效的研究手段。
  7. 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。
  8. 2. after the appropriate mathematical and physical model was proposed, the numerical calculation was processed in fluent

    2 .根據進氣道內的流動特性，建立適當的數學和物理模型，用flunt進行數值計算。
  9. Numerical simulation by cfd was carried out to understand the hot current behavior in a tunnel with longitudinal ventilation. it becomes clear that fire source modeling is very important because the hot current behavior is strongly affected by the fire source position and is sensitive to methods in the modeling of the fire source. the flame area which has developed from the fire source is an area of chemical reaction caused by combustion. even if grids in the vicinity of the fire source are made fine, it was difficult to simulate the heat generation area with consideration to this chemical reaction through using a method for setting the heat release rate simply on the fire source surface. therefore, we proposed a method adopting the knowledge on flame shape under the longitudinal ventilation and incorporating it into numerical simulation and it showed a good agreement with the experimental results. it was shown through experiments in a tunnel with longitudinal ventilation that the hot current developed toward the tunnel center downwind from the fire source near a wall. the cause was investigated by numerical simulation and it became clear from the results that the spiral air by the fire plume created a vortex in the crevice between the wall and the plume

    運用cfd進行數字模擬，以了解縱向通風隧道內熱煙氣流的特性.通過模擬發現對火源進行模擬非常重要，熱煙氣流特性受火源位置的影響很大，並且對火源模擬方法很敏感.火源生成的火焰區是燃燒引起的化學反應區域.即使火源附近的木垛排列完好，也很難在考慮這些化學反應條件下模擬熱生成區域.建議考慮縱向通風隧道內火焰形狀並對它進行數字模擬.模擬結果與試驗結果非常吻合.試驗證明，在縱向通風隧道內，熱煙氣流從靠近墻體火源處順風向隧道中心蔓延.數字模擬結果發現，火災羽流造成的螺旋上升空氣會在墻體和羽流之間形成一個渦流區
  10. Abstract : numerical simulation by cfd was carried out to understand the hot current behavior in a tunnel with longitudinal ventilation. it becomes clear that fire source modeling is very important because the hot current behavior is strongly affected by the fire source position and is sensitive to methods in the modeling of the fire source. the flame area which has developed from the fire source is an area of chemical reaction caused by combustion. even if grids in the vicinity of the fire source are made fine, it was difficult to simulate the heat generation area with consideration to this chemical reaction through using a method for setting the heat release rate simply on the fire source surface. therefore, we proposed a method adopting the knowledge on flame shape under the longitudinal ventilation and incorporating it into numerical simulation and it showed a good agreement with the experimental results. it was shown through experiments in a tunnel with longitudinal ventilation that the hot current developed toward the tunnel center downwind from the fire source near a wall. the cause was investigated by numerical simulation and it became clear from the results that the spiral air by the fire plume created a vortex in the crevice between the wall and the plume

    文摘:運用cfd進行數字模擬，以了解縱向通風隧道內熱煙氣流的特性.通過模擬發現對火源進行模擬非常重要，熱煙氣流特性受火源位置的影響很大，並且對火源模擬方法很敏感.火源生成的火焰區是燃燒引起的化學反應區域.即使火源附近的木垛排列完好，也很難在考慮這些化學反應條件下模擬熱生成區域.建議考慮縱向通風隧道內火焰形狀並對它進行數字模擬.模擬結果與試驗結果非常吻合.試驗證明，在縱向通風隧道內，熱煙氣流從靠近墻體火源處順風向隧道中心蔓延.數字模擬結果發現，火災羽流造成的螺旋上升空氣會在墻體和羽流之間形成一個渦流區
  11. Firstly, the author, in this essay, has proceeded from the compiling principles of the trajectory report and the actual situations of the field troops, analyzed the defects and shortcomings of the present compilation of the trajectory report, and described systematically the principles and procedures of computing the layer power by the methods of statistical analyses. thereupon, a complete model of computing the layer power has been established and the computation results of the proximate layer power have been found out by simplified process. secondly, the comparison computation has been conducted in accordance with the paired projectiles of 122mm, 152mm and 155mm guns equipped in our army, and test and analyses of the research results have been carried out

    論文中，作者首先從彈道通報的編制原理和部隊的實際使用情況入手，分析其缺陷，進而結合統計分析的一般方法系統地描述了計算層權的原理及過程，建立了計算精確層權、近似層權的完整模型，並通過計算與統計，詳細給出了專用及通用近似層權的計算結果，然後針對我軍裝備的122mm 、 152mm 、 155mm彈丸進行對比計算，對研究結果進行了檢驗與分析；最後，針對計算機氣象通報的特點，論證了對其作進一步改進的可行性與必要性，提出了相應的措施。
  12. Combining physical experiments and theoretical analysis, this literature has performed thorough research on gas properties of delivery pipeline system, pressure current rush to interception air - mass in pressure pipeline, water hammer with gas that happens with gas releasing and liquid column separating

    本論文通過物理試驗與理論分析對輸水管道系統中的氣體特性、壓力水流沖擊截留氣團和包含氣體釋放和液柱分離現象的含氣水錘進行了深入研究。
  13. 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。
  14. This dissertation has on the research and design of a micro turbine engine as background and it is for the purpose of comprehending viscous flow behaviors in micro scaled conditions and that in the mini - turbine cascades. a mini wind tunnel is designed and set up which also can be used in other micro flow experiments. on the basis of this mini wind tunnel, three mini flow experiments, including micro jet experiment, micro boundary layer experiment and mini - turbine cascades experiment, have been carried out

    本文以某型微型渦輪噴氣發動機研製為背景，以認識微尺度下粘性流體流動狀態及其機理和微渦輪葉柵通道內部流動特性為目的，設計並搭建了除本實驗外還可供其他流體力學實驗使用的微型風洞，並在該微型風洞基礎上進行了微尺度射流實驗、微尺度壁面邊界層實驗和微尺度渦輪葉柵實驗。
  15. Research on pressure current rush to interception air - mass in pipeline based on the study of gas properties in pipeline system, the research which was performed through physical experiments and mathematical modeling calculation, current rush to interception air - mass contents in different pipeline, the influences of different stop gate closing - velocities to pressure current rush to interception air - mass in pipeline and some other factors, were given much consideration on the influence of current rush to interception air - mass in pressure pipeline

    2 、輸水管道系統中壓力水流沖擊氣團研究在對輸水管道系統氣體特性研究的基礎上，通過試驗對壓力水流沖擊截留氣團進行了研究，著重研究不同的截留氣團含量、不同的閥門關閉速度等對水流沖擊管道截留氣團的影響。
  16. On the study of supersonic inlet optimization algorithm, first, the inlet performance curve is converted to facilitate curve interpolation. then, with this converted performance curve, inlet optimization problem is converted to a simple nonlinear constrained optimization problem

    在對超音速進氣道進行優化時，首先對進氣道特性進行適當變換，然後利用變換后的特性，將進氣道的優化問題轉化為一個易於求解的單變量約束非線性優化問題進行求解。
  17. A useful technique has been provided and developed for the researching and analyzing the factors and variation of flow field in the intake duct of diesel engine. to find out a new method to measure flow measurement, different intake duct on different conditions are experimented and researched by real - time holographic interferometry. real - time holography interferometry has many characteristics, such as high precision, non - destructive, high contrast of interference fringes and full field test

    該方法具有精度高、非接觸、條紋對比度好、對被測物體形狀和表面無特殊要求的特點，實驗了對三維非定常流動過程的可視化實時採集，為了解和分析不同流量、不同結構參數下進氣道內氣流運動狀態和流動特性的變化關系及其影響因素提供了一種有效的測試手段。
  18. 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。
  19. The results attained are as follows. on account of the strongly coupling character of parameters which have an effect on scramjet performance, the approximate evaluation models of scramjet inlet diffusion performance and the ignition problem in direct - connected experiments are established by neural network methodology

    針對發動機性能影響因素強烈耦合的特點，採用bpnn和rbnn神經網路方法，分別建立了超燃沖壓發動機進氣道擴壓性能和直連式發動機點火性能的神經網路近似評估模型，得到了很好的逼近效果和預測能力。
  20. The primary work of this paper is as follow : three aspects are analyzed in detail as to the characteristics of integral rocket - ramjet, which include : a. the matching for inlet shape and missile configuration ; b. the influence on missile conceptual performance caused by the number and position of inlet ; c

    具體表現在如下幾個方面： （ 1 ）針對整體式沖壓發動機的特點，詳細分析了進氣道型式與導彈總體布局的匹配關系、進氣道數目及其安裝位置對導彈總體性能的影響、沖壓發動機和固體助推器的一體化等彈機一體化設計的問題。
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