馬赫數計 的英文怎麼說

中文拼音 [mǎhèshǔjì]
馬赫數計 英文
mach indicator
  • 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
  • 計 : Ⅰ動詞1 （計算） count; compute; calculate; number 2 （設想; 打算） plan; plot Ⅱ名詞1 （測量或計算...
  1. 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。
  2. 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。
  3. 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。
  4. The verification results show that the theoretical analysis of nozzle is correct, the curve of the nozzle contour satisfies the design requirements, and the designed nozzle has reached the general industry criterion

    給出了流場的馬赫數分佈和出口截面的馬赫數。校核結果表明噴管理論分析正確，噴管型面曲線符合設計要求，噴管設計達到行業標準。
  5. 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。
  6. Schedule for tables relating to altitudes, airspeed and mach numbers for use in aeronautical instrument design and calibration

    航空儀表設計和校準用高度空速和馬赫數表
  7. 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。
  8. 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。
  9. The equal density and pressure of free streams are chosen to study the effect of compressibility on the mixing layer

    計算選取來流密度和壓力相等，對流馬赫數從0 . 2到1 . 2 ，以研究壓縮性對混合層流動的影響。
  10. With high temperature and high pressure in nozzle of wind tunnel, the effect of variable specific heat on nozzle design must be considered

    本文針對超音速、高超音速噴管內馬赫數、溫度變化劇烈的特點，研究了比熱容變化對設計噴管型面產生的影響。
  11. 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。
  12. 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。
  13. The numerical method to solve the equation for spatial amplification theory is described in detail. deduced first - order system equations from spatial instability theory and its eigenvalue problem are solved and neutral lines varied with mach numbers are given

    運用穩定性理論的空間放大理論，建立穩定性方程，得到一個六元一階方程組，然後求解該一階系統，計算並得到不同馬赫數下的中性穩定曲線，基於此得到不同馬赫數下流場的臨界失穩點和穩定區域。
  14. The results show that to design a supersonic / hypersonic nozzle of wind tunnel must consider the effect of variable specific heat, which gives reference to nozzle and wind tunnel design

    考慮這一因素后，噴管出口馬赫數接近設計馬赫數，其設計精度有較大提高。本方法可為超音速高超聲速噴管設計和反設計提供參考。
  15. To prove the accuracy of the mach number, and the parameter homogeneity of the design nozzle " s exit, cfd calculate has carried on the design results. under the condition of supersonic and hypersonic flow, and a certain range of temperature, and mach number, the conclusion of the influence of specific heat to nozzle design is drawn

    為了驗證所設計的噴管出口馬赫數的大小和噴管出口流場的均勻性，採用nnd格式和b l湍流模型求解雷諾平均n - s方程，對設計結果進行了cfd驗算，得出了在一定溫度范圍內，超音速、高超聲速流動的條件下，不同馬赫數范圍內變比熱容對噴管型面和噴管出口馬赫數的影響。
  16. 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。
  17. 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。
  18. 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
  19. 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。
  20. 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。
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