馬赫值 的英文怎麼說

中文拼音 [mǎhèzhí]
馬赫值 英文
mach
  • 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...
  1. They also exported them to all the kings of the hittites and of the arameans

    赫人諸王和亞蘭諸王所買的車馬，也是按這價值經他們手買來的。
  2. The move comes amid fierce fighting between hamas and rival fatah

    正值哈馬斯和對手法塔赫進行激烈的戰斗期間。
  3. 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。
  4. The main working procedure of the fiber - optic sensor is : the sensing element detects the acceleration signal, this signal modulates the phase of the wave, and the phase change is corresponding to the acceleration signal

    該光纖加速度計的工作過程為:敏感元件感受外界的加速度信號，並把它轉化成馬赫-增德爾干涉儀測量臂的拉伸或壓縮，從而引起測量臂中的光波相位變化，相位變化量即代表被測加速度值。
  5. Numerical fluxes considered in the explicit portion of the algorithm were evaluated by an implicit high - order compact scheme to augment stability. meanwhile, an implicit high - order compact numerical filter was used

    顯式一邊的空間導數採用具有較高精度和良好數值穩定性的隱式高階緊致差分格式，同時採用適于低馬赫數流動計算的隱式高階數值過濾方法。
  6. 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。
  7. In the results of eight 2d simulation cases with convective mach number ranged from 0. 2 to 1. 0 the mean velocities and the thickness growth rates are in good agreement with experimental results, but the turbulent fluctuation intensities are larger

    對對流馬赫數從0 . 2到1 . 0的混合層的二維數值研究表明，平均速度分佈和擴張率與實驗結果相符合，但湍流脈動強度偏大。
  8. "go on, phyl, " said herb, feeling there must be something in her if the great max judkins thought her worth his attention.

    「去吧，菲兒」赫布說。他覺得要是連了不起的馬克斯賈金斯都認為她還值得看一眼的話，那兒她準是有一些可取的地方。
  9. In this thesis, hypersonic sidewall compression inlet ' s self - starting characteristics are numerical simulated and tested. with increasing mach number of inflow gradually, the hypersonic sidewall compression inlets can self - start. compared with the hypersonic sidewall compression inlet starting directly, characteristics are different. moving cowl, decreasing interior contraction ratio also can realize the hypersonic sidewall compression inlet ' s self - starting because of separation bubble on sidewall spilling out

    其次，在數值模擬結果的基礎上，設計了實驗模型和裝置並在馬赫3 . 85的風洞中進行了移動唇口板減小內收縮比實現側壓式進氣道自起動的風洞實驗，驗證了數值模擬的結果。
  10. At the same time this paper calculates the effect of train velocity on noise propagation, when mach number is 0. 1, sound velocity less effects on noise level ; when mach number is 0. 4, the difference value is about 2db whether to consider the sound velocity. so when the train velocity is not very high, the effect of sound velocity may not be considered

    本文同時計算了列車運行速度對噪聲傳播的影響，當馬赫數為0 . 1時，聲音的傳播速度對聲級的影響是很小的，當馬赫數為0 . 4時，考慮聲速與不考慮聲速影響的最大值的差值大約為2db左右，因此在列車速度不是很高的情況下可以不考慮聲速的影響。
  11. The two - dimensional axisymmetric subsonic - transonic - supersonic flow in an experimental arcjet thruster is simulated numerically using flux vector splitting method. the profiles of density, velocity, temperature, pressure and mach number can be obtained by the computation. the computation grid and some computed results are given here. the test equipment such as power supply system, ignition system, propellant supply system, arcjet thruster, thrust measuring device and vacuum system are introduced briefly. some working phenomena of the arcjet are observed and discussed. three different kinds of instability appeared in the process of the experiments. except some important parameters are measured, it is found that the operating stability of argon is better than that of nitrogen

    對一實驗電弧加熱式發動機二維軸對稱亞跨超音速流動進行了數值模擬，所採用的方法是矢通量分裂演算法.通過計算可以得出密度、速度、溫度、壓力和馬赫數的分佈.給出了計算所使用的網格和一些計算結果.簡要介紹了實驗所使用的設備，如電源系統、點火系統、推進劑供給系統、電弧加熱式發動機、推力測量裝置和真空系統.對所觀察到的一些工作現象進行了討論.有三種不同的不穩定性出現于實驗過程.除了所測量的一些重要參數，通過實驗發現氬比氮工作更穩定
  12. Nobuaki uratani and tom kaczmarek each had it 114 - 114, while john stewart saw a rahman rout, 117 - 111. the associated press scored it 114 - 113 for rahman

    諾布阿齊?烏拉塔尼和湯姆?卡茲馬萊克每人都是114 - 114 ，而約翰?斯德沃特認為拉赫曼贏117 - 111 。美聯社統計分值為114 - 113判拉赫曼勝。
  13. At different attack angles, mach numbers and ramp angles, the numerical calculations of inner and external flow field are performed for an adjustable mixed compression inlet

    摘要對某可調混壓進氣道在不同攻角、不同馬赫數、不同斜板角度下進行了大量的數值計算。
  14. The ratio of mach number between lateral jet and free flow induce intensity degree of jet interaction. it has no obvious difference between two interactions with two types of nozzle exit configuration, rectangle and ellipse. the shock in front of jet results in increase of shock resistance and the jet ejection causes increase of base resistance

    研究表明，側噴流與來流馬赫數之比是影響繞流場的重要因素，該值越大則側噴干擾越強烈，矩形和橢圓形兩種側噴口形狀對側噴流場干擾波系的影響並不明顯。
  15. Because of ferrari ' s 60th anniversary schumacher was invited to complete a few laps at fiorano in the championship winning car the f2004

    由於時值法拉利的60周年慶典，舒馬赫被邀請到現場駕駛他在2004年奪冠時曾使用過的f2004賽車參加試車。
  16. The main results are : supersonic region and subsonic region can co - exist in flow path simultaneously, subsonic flow is insignificance for engine performance ; total pressure of primary rocket should be decreased when mach number is increased. in the experimental aspect, some components of ejectorjet experimental system were improved, ejectorjet experiments using alcohol as secondary fuel were conducted

    由數值計算獲得的結論為：引射火箭內的一般流態為超音速區與亞音速區共存，亞音速區不具備做功能力；飛行馬赫數增大，引射火箭內更易於產生壅塞；為了獲得最佳的性能，隨著飛行馬赫數的提高，應當降低一次火箭的工作壓強。
  17. Finally, the two dimensional flow in the diffuser is calculated, the results show that the change of ma makes an effect to the performance of the diffuser. owing to the accretion of ma, the action of oblique shock waves and the boundary layer pricks up, the flow separates from the wall where the shock waves impinge on the boundary layer more quickly, the cluster of diamond shock waves becomes larger. moreover, by comparing the change of flow field under different structure parameter, it is found that the augment of length of constant area section alter the structure of fluid field little, a smaller area ratio and larger angle of compression section make the diffuser working better

    最後，針對擴壓器中的二維流場進行了數值模擬，結果表明馬赫數對擴壓器性能影響較大，隨著馬赫數的增大，擴壓器管道內激波-附面層干擾加劇，流動從附面層分離相應加劇，激波串數目增多;通過比較不同結構參數下的擴壓器內流場，發現等直段長度的變化幾乎沒有改變流場結構，只是對局部流場稍有影響，並且在其它參數不變的情況下，一定范圍內減小面積比a2 / a1和增大收縮角有利於擴壓器性能的提高。
  18. In order to compare with the extreme of dynamic solutions when the mach number approaches zero, i. e. the quasi - static propagation, the corresponding quasi - static problem is also studied asymptotically in the paper. the governing equations of crack - tip field are derived, and numerical solutions are obtained by selections of typical parameter values with combination of boundary conditions of each problem

    採用這種率敏感型本構關系，為了與馬赫數趨于零時動態解的極限情況? ?準靜態擴展情況作對比，本文還對相應的準靜態問題進行了漸近分析，推導了裂尖場的控制方程，並選取典型的特徵參數，結合問題的邊界條件進行了數值求解。
  19. Secondly, author find the relationship between tow - factor and incentive methods, and assume an application model. thirdly, author gather a set of important information which is propitious to analyze the relationship of personality and incentive methods. fourthly, after the analysis of data, we find the order of different personality people favor incentive methods and the order of different incentive methods adapt to personality, then analysis by synthesis

    本論文的研究成果主要有以下幾點：一是分析馬斯洛劃分的需要層次與激勵方法的對應關系，並設計需要層次與激勵方法應用模型；二是分析赫爾伯茨劃分的雙因素與激勵方法的對應關系，並設計出雙因素與激勵方法應用模型；三是通過調研得到一組不同人格對激勵方法偏好的重要現實數據；四是通過對數據的分析，得到不同人格對特定激勵方法的偏好順序、不同激勵方法對特定人格的影響順序，運用兩組順序，對人格與激勵方法進行了具有實用價值的綜合分析。
  20. 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。
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