mach number 中文意思是什麼

mach number 解釋
馬赫數
  • mach : n. 【物理學】馬赫〈超高速單位，馬赫數，＝Mach number〉。
  • number : n 1 數；數字；〈pl 〉算術。2 （汽車等的）號碼；第…，第…卷，第…期〈通常略作 No （復數 Nos ），用於...
  1. Deng x g, zhuang f g, mao m l. on low mach number perfect gas flow calculations [ r ], aiaa paper 99 - 3317

    鄧小剛.粘性超聲速復雜氣動力干擾的數值模擬[ d ] : [博士學位論文] ，中國空氣動力研究與發展中心， 1991
  2. 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。
  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. The dynamic performance of a ram air system will vary with mach number and altitude and this tends to follow the aerodynamic characteristics of the missile.

    像導彈空氣動力特性一樣，沖壓空氣式系統的動態特性隨馬赫數和高度的變化而變化。
  5. In this paper, some flows around naca 0012 aerofoil, m6 wing and two different blunt vehicles are simulated, the results show that the present algorithm possesses good characteristics and capability for normal mach number and for hypersonic of simple configurations

    通過對naca0012翼型、 m6機翼、鈍頭以及雙鈍錐?柱體的算例驗證，本文能很好的解決一般馬赫數問題，能夠很好的求解簡單外形的高超聲速問題，對于復雜外形飛行器還需要進一步進行研究驗證。
  6. Supercritical wings have been widely used on modern civil airplanes and military transports due to their higher aerodynamic efficiency, higher cruising mach number and greater relative thickness

    超臨界機翼由於其具有較高的氣動效率、較高的巡航馬赫數及較大的機翼相對厚度而被廣泛應用於新一代民用飛機及軍用運輸機上。
  7. In the range of flight mach number mo = 3 ~ 7, in order to take the advantage of ramjet and scramjet, a fix - shaped dual - mode scramjet, in which both subsonic and supersonic combustion can be obtained, is used for hypersonic vehicle

    在飛行馬赫數m _ = 3 - 7的范圍內，為充分發揮沖壓發動機的性能優勢，高超聲速飛行器採用了既能在亞聲速燃燒模態，又能在超聲速燃燒模態下工作的固定幾何形狀的雙模態沖壓發動機。
  8. 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。
  9. The results show : laser beam far field intensity distribution deflect to the wave length increasing direction, the influence to laser beam far field intensity distribution of different inflow mach number is little than the influence of different inflow pressure ; flow field has more aberration to 1. 315um laser beam than to 10. 6um laser beam

    研究表明激光束遠場強度分佈都向流場光程增大的方向偏折，噴流出口馬赫數的變化對激光束遠場強度分佈的影響較小，噴流出口壓力的變化對激光束遠場強度分佈的影響較強；在相同的流場結構下，流場對波長1 . 315 m激光束的干擾要明顯強于對波長10 . 6 m激光束的干擾。
  10. 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。
  11. The effect of area ratio, mach number, total pressure of primary rocket and geometry structure of primary rocket on ejectorjet performance was studied

    通過數值計算研究了引射火箭堵塞比、來流馬赫數、一次火箭燃燒室總壓、一次火箭構型對引射火箭性能的影響。
  12. Then to calculate the time span that airplane arrive the aim point, by adjusting descent mach number, descent cas and top - of - descent point

    在此基礎上，通過調節下降馬赫數ma 、下降校正表速cas和開始下降點top ，算出飛機飛到目標點的時間區段。
  13. 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。
  14. There are shocklets in the mixing layer with convective mach number 1. 2

    高對流馬赫數混合層中存在較弱的小激波間斷。
  15. Valve outlet mach number

    閥出口馬赫數
  16. The profiles of density, velocity, temperature, pressure and mach number can be obtained by the computation

    通過計算可以得出密度、速度、溫度、壓力和馬赫數的分佈。
  17. In among, the control system of mach number is a core system, which guarantee realizing performance for nf - 6 wind tunnel

    其中馬赫數控制系統是保證整個風洞性能指標的核心系統。
  18. The effects of such elements as primary flow total pressure, flow rate, degree of fuel rich, nozzle structure, flying speed and secondary combustion on ejecting mode performance were researched. it was found that thrust augmentation can be achieved on the condition that the flying mach number is above 0. 7. to deeply analyze thrust augmentation mechanism in low speed range, the research was further continued by changing secondary combustion organization and aft - body configuration

    研究了一次流總壓、流量、富燃程度、噴管結構、二次流來流速度、二次燃燒組織對引射模態性能的影響，發現實驗樣機構型在0 . 7ma以上的飛行條件下可以獲得推力增強，而在0 . 7ma以下無推力增強。
  19. 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。
  20. Then, the one dimensional model is used to study on some factors ( viscosity, the heat given out by the chemical reaction in the chemical laser ) which bring the loss of the total pressure. the answer shows that increasing the mach number at out of the nozzles in the laser can reduce the loss of the total pressure

    在此基礎上，用簡化的一維模型研究了引起激光器總壓損失的幾個要素，它們是:噴管的粘性損失，光腔內的放熱化學反應。研究的結果表明，提高噴管出口馬赫數有利於減少這些因素導致的總壓損失。
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