氣流馬赫數 的英文怎麼說

中文拼音 [qìliúmǎhèshǔ]
氣流馬赫數 英文
flow mach number
  • 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...
  • 流 : Ⅰ動1 （液體移動; 流動） flow 2 （移動不定） drift; move; wander 3 （流傳; 傳播） spread 4 （向壞...
  • 馬 : Ⅰ名詞1 [動物學] （哺乳動物） horse 2 （象棋棋子） horse one of the pieces in chinese chess3 （姓...
  • 赫 : Ⅰ形1 （顯著; 盛大） conspicuous; grand 2 （紅如火燒） bright flaming redⅡ名詞1 [電學] （頻率單位...
  • 數 : 數副詞（屢次） frequently; repeatedly
  • 氣流 : 1 [氣象學] air current; airflow; wind current; airstream2 [語言學] breath氣流紡紗 open end spinni...
  1. 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。
  2. In this dissertation, the pulse jet style, the influence on the shock wave, the flow in the tube and the cooling effect was deeply studied theoretically and experimentally. the influence of the pulse jet style on the forming of shock wave and the shock wave intensity was explored. the initial disconnection style in oscillating tube vented and the initial disconnection breakdown was proposed by different pulse jet style

    本文對脈動射流的型式及其對激波、管內流動及冷效應的影響進行了較系統的理論和實驗研究，主要包括:探討了脈動射流的型式對形成管內激波形成及激波強度的影響，給出了不同脈動射流的型式下振蕩管開口端初始間斷的類型，對初始間斷進行了分解，導出了包含進氣、排氣參數及工質物性參數的管內入射激波馬赫數mj的表達式，給出了管內激波形成的三種原因及其所對應的脈動射流型式和具體的工作狀態。
  3. The results prove that : ( 1 ) when the mach number of the flow at the exit increases, the total pressure recovery decreases, and the circular steady total pressure distortion coefficient, turbulence intensity and synthesis distortion increase

    研究結果表明： （ 1 ）地面工作狀態下，隨著出口馬赫數的增加，蛇形進氣道出口截面的總壓恢復系數不斷下降，而穩態周向畸變指數、紊流度和綜合畸變指數均上升，穩態徑向畸變指數變化不大。
  4. The convective term is solved by ausm + ( a sequel to ausm which means " the advection upstream splitting method " ). the 7 species 8 steps model and 7 species 7 steps model of hydrogen / air is used in the hydrogen reacting flowfield, the 9 species 5 steps model of methane, the 10 species 10 steps model of ethane and the 10 species 13 steps model of kerosene are used in the hydrocarbon reacting flowfield, the results of the distributions of velocity, mach number, pressure, static temperature, total temperature, species mass fraction and the combustion efficiency are gained, and the numerical results of the pressure of hydrogen and methane are compared with those of the experiment

    計算中通量項採用ausm +通量分裂格式，氫反應流場採用氫/空氣的七組元八方程模型和七組元七方程模型，碳氫反應流場採用甲烷的九組元五方程模型、乙烯的十組元十方程模型和煤油的十組元十三方程模型，得出了超燃發動機燃燒室流場的速度、馬赫數、壓力、靜溫、總溫和組元質量分數分佈及燃燒效率等性能參數，其中氫和甲烷的計算壓力分佈與實驗結果進行了比較。
  5. 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。
  6. Abstract : with an optical probe based on the principle of multi - wavelength light extinction, size and concentration of droplet were measured in a transonic wind tunnel. this paper presents the measurement results

    文摘:應用基於多波長消光法原理發展的光學探針，測量了跨聲速風洞中不同馬赫數濕空氣流自發凝結形成的水滴尺寸及濃度，並給出了實驗結果。
  7. 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。
  8. The velocity distributions, the relative mach number distributions and the flow trace distributions are visualized, and the reasons, which cause bad aerodynamic losses and make the flowfield complicated, are analyzed, including wake, secondary flow, separated flow and the interaction between shock and boundary layer

    顯示壓氣機內的速度場、相對馬赫數分佈及流動跡線分佈等，並分析造成嚴重損失及使流場趨于復雜紊亂的原因，包括尾跡、二次流、分離流及激波/附面層干擾等現象。
  9. Variations in pressure with and without aeration in cavitation region are measured and the compressible characteristics of pressure waveforms and relation between mach number and compression ratio are analyzed ; the time - averaged pressure profiles of different air concentration in cavitation erosion region are measured, the variations of the pressure with air concentration and effects of back pressure on cavitation erosion are analyzed ; the relations between least air concentration to prevent cavitation erosion and flow velocity are proposed ; the cavitation numbers with and without aeration in cavitation region are compared

    實測了空化區摻氣前後壓力的變化，分析了壓力波形的可壓縮流特徵以及馬赫數與壓縮比的關系；實測了空蝕區不同摻氣濃度的時均壓力分佈，分析了壓力隨摻氣濃度的變化及背壓對空蝕的影響；提出減免空蝕的最低摻氣濃度與流速的關系，比較了摻氣前後水流的空化數。
  10. In this paper, maccormack explicit time - split scheme, baldwin - lomax algebraic turbulent model and two - steps hydrogen - air nonequilibrium chemical kinetics model are employed to simulate the 2 - d flow fields in a fixed geometry scramjet combustor in different injecting way of fuel in different flight conditions. the results show, in the same entrance condition, the operating mode of scramjet combustor is influenced by the control of fuel

    本文採用maccormack顯式時間分裂法、 b - l代數渦粘性湍流模型及氫-空氣兩步非平衡化學動力學反應模型，模擬了在不同的飛行馬赫數條件下，固定幾何的雙模態燃燒室在不同供油規律下的二維燃燒流場。
  11. The relevance functions between total pressure recover coefficient and the parameters ( mach number, angle of attack, flow coefficient, angle of sideslip ) for subsonic submerged inlet in turbojet and turbofan engine were investigated

    摘要根據某埋入式進氣道試驗數據建立了計算埋入式亞聲速進氣道總壓恢復系數的經驗公式，表現為關于馬赫數、流量系數、攻角、側滑角的函數。
  12. Numerical simulation shows that, at small and medium c, multi - slot circulation control can increase the lift of the airfoil and reduce the amount of the energy expense, and that it can improve the aerodynamic performance of cca at higher mach numbers by avoiding the “ compressibility stall ”

    結果表明，多噴口環量控制方法可以在中、小c吹氣時提高翼型的升力和減小能耗，並能改善環量控制翼型在較高來流馬赫數下的氣動性能，避免「壓縮性失速」 。
  13. The balanceable piston theory and perfect gas model are used as building block to design tunnel, and the resulting tunnel can generate uniform flow, which can provide long experimental time with high mach number, given enthalpy and reynolds number, thus, the scramjet and ramjet aircraft can be studied in this tunnel

    採用理想的平衡活塞運行理論和完全氣體模型，該風洞可以產生高馬赫數、一定焓值和re數、實驗時間較長的均勻流動，滿足超燃、亞燃現象的研究。
  14. After redistributing its surface, three - dimensional body - fitted grid is generated by solving elliptic partial differential equations, namely elliptic grid generation. the program of computing n - s equation is used to get the desiring results of varieties of attack angles and velocities. it is concluded that the results accord with the aerodynamics rules, so the computing results will instruct the experiment to some degree

    採用求解三維n - s方程的計算程序，計算了不同來流馬赫數下和不同攻角下的布撒器的流場，並分析了來流參數對計算結果的影響，分析結果表明計算所得的結果符合空氣動力學的基本規律，計算結果對實驗具有重要的指導意義。
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