進氣角 的英文怎麼說

中文拼音 [jìnqìjiǎo]
進氣角 英文
flow inlet angle
  • 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...
  • 角 : 角Ⅰ名詞1 （牛、羊、 鹿等頭上長出的堅硬的東西） horn 2 （古時軍中吹的樂器） bugle; horn 3 （形狀像...
  • 進氣 : air admission; admission; inlet; onflow; charging; access of air; admittance; air in; air intake;...
  1. The design point of the designed forebody / inlet is flight mach number m = 6 and flight attitude h = 25km. the three - ramp, mixed external and internal compression hypersonic / inlet is chosen as representative geometry to be designed. nine types of hypersonic / inlet model with difference forebody length and total turning angle are obtained that the incidence angle of the first ramp and height of isolator are given

    根據飛行任務要求，以飛行馬赫數6 ，飛行高度25km為設計點，給定前體預壓縮角、隔離段高度，對具有不同前體長度和不同總壓縮轉角的帶隔離段的前體進氣道進行了設計。
  2. 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。
  3. 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。
  4. 4 ) in a pre - swirl rotator - stator cavities with discrete pre - swirl nozzles and blade - cooling entry holes, the influences of pre - swirl angle and flow parameter on the flow and heat transfer characteristics were numerically investigated. the correlation for average nusselt number vs rotating reynold number or non - dimensional mass flowrate were established. the results show that : advantage of per - swirl inflow is the effect of cooling the blade - cooling entry holes ; pre - swirl inflow increases heat transfer in rotating disk of pre - swirl chamber ; as pre - swirl angle increases, local nusselt number decreases in pre - swirl chamber ; the temperature of stator of inner rotator - stator chamber and per - swirl chamber decreases as rotating reynold number increases ; when the axial mass flowrate maintains constant, heat transfer in the rotating disk of inner rotator - stator cavities does n ' t change as per - swirl mass flowrate increases, while heat transfer in the rotating disk of per - swirl chamber increases ; when the pre - swirl mass flowrate maintains constant, change of the axial mass flowrate has effect on the whole cavity

    結果表明，預旋進氣的優點在於增強了葉片冷卻孔附近的對流換熱效果，局部努謝爾數隨預旋角的增大而有所減小；隨旋轉雷諾數的增加，不論是內轉靜腔室還是預旋腔室的靜盤上的溫度都不同程度的降低：當軸向中心進氣質量流量不變時，隨預旋進氣的質量流量增加，內轉靜腔室的轉盤盤面上的換熱基本沒有變化，而預旋腔室的轉盤盤面上的換熱效果增強；當預旋進氣質量流量不變時，軸向中心進氣的質量流量的改變對整個盤腔都有影響。
  5. In addition to a longer nose, aerodynamic modifications feature kfir - style small nose side - strakes to prevent yaw departure at high aoa, a pair of fixed delta canards on the upper parts of the air intakes, dog - tooth outboard leading - edge extensions, and short fences replacing leading - edge slots

    除了一個加長的機鼻外，氣動布局的修改包括：在機鼻兩則裝上可以防止在高攻角下脫離偏航的「幼獅」式小邊條，一對固定在進氣道的三角鴨翼，鋸齒型外翼前緣，和代替前緣翼槽的短翼刀。
  6. In this experiment, adjusting the throttle to the specific position, and letting engine rotary speed change from the lowest to the highest, at the same time, the data of the water temperature, the fuel temperature, the air press and the rotary speed can be noted. moreover, we can measure the fuel quantity and the ignition angle

    實驗中，調節節氣門在特定位置，並讓發動機的速度依次從最低變化到最高，同時記錄水溫、油溫、進氣壓力和轉速等數據，還可以測出相應的噴油量、點火提前角。
  7. We got to the corner store and entered to the smell of fresh bread baking in the back

    我們走進街角的小商店，店后頭正烤著麵包，香氣迎?面撲來。
  8. Yaojung shiao and john j. moskwa, “ cylinder pressure and combustion heat release estimation for si engine diagnostic using nonlinear sliding observers ”, ieee trans. vol3, no1, 1995

    陳建霖，汽油引擎進氣壓力及點火角度對引擎性能影響之電腦模擬，碩士論文，雲林科技大學，雲林， 2003 。
  9. On the basis of these results, the relations of total - pressure recovery coefficient or flow coefficient and flight mach number, angle of attack and the second movable wedge angle of the inlet have been founded by hypersurface fitting, then the mathematical model of the inlet is established

    根據流場計算結果並利用超曲面擬合方法建立了進氣道總壓恢復系數、流量系數與飛行馬赫數、進氣道攻角及二級可調斜板角度之間的關系，由此得到了二元混壓式超聲速進氣道數學模型。
  10. Inlet advance crank angle

    進氣提前角
  11. Intake advance angle

    進氣提前角
  12. Intake lag angle

    進氣遲后角
  13. The intake lag angle of the engine is optimized, and the dynamic effects of intake pipes and exhaust pipes to the improvement of motorcycle engine is applied to make the engine test performance curve approach the simulation curve

    本文介紹了從進氣晚關角及進排氣的動態效應幾方面著手，不斷改進發動機的配氣相位以及進排氣系統，使發動機的實際性能曲線逐步接近計算機模擬曲線。
  14. The existence of angle of attack reduces the inlet performance

    攻角的存在也在一定程度上降低了進氣道性能。
  15. Thermodynamic analysis on wet compression process is done in this thesis and studies are done on ideal wet compression process, actual wet compression process, water droplet evaporative rate, wet compression work, inlet evaporative cooling, wet compression efficiencies and water droplet breaking. and thermodynamic model of wet compression process is established, which gives out rules of and methods to calculate wet compression parameters

    本文從熱力學的角度對濕壓縮過程進行了分析，分別對理想濕壓縮過程、實際濕壓縮過程、水滴的蒸發速率、濕壓縮功、進氣蒸發冷卻、濕壓縮效率和水滴的破碎等進行了研究，建立了濕壓縮過程的熱力學模型，給出了濕壓縮過程狀態參數的變化規律和計算方法。
  16. On the basis of analyzing the theory of gas - solid two - phase flow, the paper put forward two ways of lightening the erosion of centrifugal fan from the point of view of initiative preventing erosion : changing fan ' s inlet and changing fan ' s impeller

    本文在分析離心風機氣固兩相流動理論的基礎上，從主動防磨角度提出了兩種減輕風機磨損的方法：改造風機進氣箱和改造風機葉輪。
  17. The full flow field characteristics of a supersonic inlet are illustrated at design conditions ; the influence of attack angle on flow field of the inlet is investigated ; b - spline theory is used to model the inlet with attack angle

    給出了設計狀態下進氣道內外流場特徵；分析了攻角變化對進氣道流場的影響；以數值模擬結果為基礎，利用b樣條理論建立了反映攻角、馬赫數及可調斜板角度變化的超聲速進氣道數學模型。
  18. 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。
  19. Inlet lag crank angle

    進氣滯后角
  20. Intake duration angle

    進氣持續角
分享友人
分享到 Line

分享到臉書