mach number method 中文意思是什麼

mach number method 解釋
馬炎數確定法
  • 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...
  • method : n 1 方法，方式；順序。2 （思想、言談上的）條理，規律，秩序。3 【生物學】分類法。4 〈M 〉【戲劇】...
  1. 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。
  2. 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。
  3. In this study a primary method for designing a waverider configuration is developed based on the approximate solution of conical flow fields. the simplified cone - derived shock wave is discussed as the basic model for design. different shapes designed from different compression angles and basic geometric coefficients at the same mach number are put into analysis

    本文基於高超聲速條件下錐型流近似解提出了高超聲速乘波構形的初步設計方案，對于不同馬赫數、壓縮角以及幾何設計參數進行了外形設計並就參數對設計外形的影響進行了討論，得到了設計參數影響外形的基本規律。
  4. 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
  5. According to the mathematic modeling principle of physical problem, the error of lattice boltzmann model is analyzed in chapter 3. the nonlinear deviation term from the navier - stokes equation is given, and the main model coefficients, such as speed of sound, viscosity and so on, are verified by numerical computation, the results show that the lattice boltzmann method has second order precision in space and in time which satisfy the engineering application, whereas, the compressible effect ca n ' t be neglected along with mach number increasing, and must be reduced or eliminated

    其次，按照物理問題數學建模的原則，對格子法的誤差進行了分析，給出了格子bgk方程再現navier - stokes方程時的壓縮誤差項，並數值驗證了格子模型的聲速及粘性系數等相關參數的精度，表明格子模型盡管具有時空二階精度，能滿足工程計算的要求，但隨著mach數增大，壓縮誤差逐漸成為主要誤差，必須予以消除。
  6. Based on it, the performances of all kinds of supersonic ejectors are compared and the effects of variety of input parameters on the performances of supersonic ejectors are discussed. the conclusion is reached, that the design scheme of small ejecting coefficient, high ejecting mach - number, combustion - gas driving should be adopted to develop high performance, high compression - ratio prs. thirdly, the method of computational fluid dynamics is used to numerically solve the flow - field of the annular supersonic ejector with or without a second flow

    接著，推導了超聲速引射器各種一維理論模型，並應用一維理論公式分析、比較了各種超聲速引射器的性能及其變化規律，全面探討了各設計參數對超聲速引射器性能的影響，得到了高性能、大壓縮比引射器系統應該採用小引射系數、高引射馬赫數、燃氣引射、優化超聲速引射器設計方案的結論。
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