模擬馬赫數 的英文怎麼說

中文拼音 [mónǐmǎhèshǔ]
模擬馬赫數 英文
dimulated mach number
  • 模 : 模名詞1. （模子） mould; pattern; matrix 2. （姓氏） a surname
  • 擬 : 動詞1. （設計; 起草） draw up; draft 2. （打算; 想要） intend; plan 3. （模仿） imitate
  • 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
  • 模擬 : imitate; simulate; analog; analogy; imitation; simulation模擬艙 boilerplate; 模擬電路 [電學] circ...
  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. 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。
  3. 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。
  4. 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。
  5. 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
  6. In order to accelerate the convergence speed, we employ the local time step, and implicit residual smoothing methods. finally, we use this method to get the steady solution of the flow around naca0012 and naca4412 airfoil at very low speed and some basic unsteady solution

    本文對在低馬赫數下繞naca0012翼型和naca4412翼型的定常流場進行了求解，結果和實驗基本吻合，並對非定常運動情況進行了初步模擬研究，得出了一些有意義的結果。
  7. 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。
  8. Abstract : according to the characteristics of high - speed water entry about the rotary projectile, an experiment plan satisfing mach similarity has been put forward for hydroballistic modeling of high - speed water entry about the rotary projectile by using dynamic equations of projectile movement and similarity theory, which can achieve the equivalent of main similarity parameters between true object and its model at atmospheric environment

    文摘:針對旋轉彈體高速入水特點，從彈體運動的動力學方程和相似理論出發，提出了模擬旋轉彈體高速入水水中彈道的馬赫相似實驗方案.該方案在大氣環境條件下，能夠實現原型和模型兩系統的主要相似準數相
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