高超聲速流 的英文怎麼說

中文拼音 [gāochāoshēngsùliú]
高超聲速流 英文
hypersonic speed flow
  • 高 : Ⅰ形容詞1 （從下向上距離大; 離地面遠） tall; high 2 （在一般標準或平均程度之上; 等級在上的） above...
  • 超 : Ⅰ動詞1 （越過; 高出） exceed; surpass; overtake 2 （在某個范圍以外; 不受限制） transcend; go beyo...
  • 速 : Ⅰ形容詞（迅速; 快） fast; rapid; quick; speedy Ⅱ名詞1 （速度） speed; velocity 2 （姓氏） a surna...
  • 流 : Ⅰ動1 （液體移動; 流動） flow 2 （移動不定） drift; move; wander 3 （流傳; 傳播） spread 4 （向壞...
  • 高超 : excellent; exquisite; superb
  1. Tahir r b, molder s and timofeev e v. unsteady starting of high number air inlets - a cfd study [ r ]. aiaa 2003 - 5191

    梁德旺，袁化成，張曉嘉.影響高超聲速進氣道起動能力的因素[ c ] / / 2005年沖壓發動機技術交流會論文集， 2005
  2. Numerical simulation of 3d hypersonic thermochemical nonequilibrium flow

    高超聲速三維熱化學非平衡流場的數值模擬
  3. Among the five kinds of nde ways ( rt, ut, et, pt, mt ), ultrasonic testing technology develops very fast because of its merits such as good orientation, strong penetration ability, higher energy and no harm to human health

    在五大常規無損檢測方法中（射線、超聲、渦流、滲透、磁粉） ，超聲波無損檢測因其方向性好、穿透能力強、能量高以及對人體無害等優點而得到了迅速發展。
  4. The tests were conducted in the hypersonic low density wind tunnel at nominal test conditions of mach 16, stagnation temperature 923k, stagnation pressure 1. 40mpa and 7. 30mpa. heat - transfer data were obtained on a hemisphere model, a sharp cone and a big blunt cone respectively by means of infrared thermal mapping techniques, that of a 0. 5mm thickness blunt cone by virtues of thermocouples. furth ermore, heat - transfer on all those models was calculated with the theoretical method

    最後在名義m _ = 16 、 t _ 0 = 923k 、 p _ 0 = 1 . 40mpa及7 . 30mpa的高超聲速低密度風洞中，利用紅外熱圖技術獲得了半球圓柱、尖錐、大鈍頭三個模型表面熱流分佈，利用薄壁法技術得到了一壁厚為0 . 5mm的鈍錐模型表面的熱流分佈，並通過工程理論方法計算了模型表面的氣動熱，把理論計算結果與上述試驗結果比較，幾者符合得較好。
  5. Although a dual - mode scramjet ' s configuration is simple and mainly consists of inlet, combustor and wake nozzle, its working process is complicated, especially in the combustor, involving a lot of subjects, including hypersonic aerodynamics, combustion chemistry, etc. the inner flow of a combustor is three - dimensional and complicated, including the interaction of shock wave, deflagration, vortex and boundary layer, and so on

    它涉及到高超聲速空氣動力學、燃燒化學、擴散傳質等多門學科；其內部的實際流動是復雜的三維流動過程，充滿著激波、膨脹波、燃燒波、各種渦系、附面層及其相互之間的干擾，因此，燃燒室問題是整個發動機研究的關鍵所在。
  6. Numerical method on unstructured hybrid grid for hypersonic flows with magnetic fields

    非結構混合網格高超聲速繞流與磁場干擾數值模擬
  7. According to the high dispersedness and low precision of measurements when using the traditional time difference method in small diameter and low flow rates conditon, this paper brings forward a new method based on high - speed data acquisition technique. the time difference comes out accurately with high resolving ability of time by using the method and the signal processing algorithms. the developed ultrasonic detection system is composed of two ultrasonic detectors, a transmitting and receiving ultrasonic unit, a high - speed data acquisition unit and a computer

    本文針對傳統的時差法在小管徑、低流速測量時，具有測時結果分散性大、測量精度受計數頻率的影響大等不足，創造性地把高速數據採集技術應用在超聲波流量、壓力測量上，用信號處理演算法求時差，使時差成為一個統計量，有效地克服了超聲波傳統時差法測量精度差、不能測量小管徑、低流速流體流量的缺點，提高了時差測量的解析度和精度。
  8. The flowfields around the reentry blunt body are simulated numerically by solving the navier - stokes with the various thermal and chemical model, such as perfect gas model, vibrational excitation model, equilibrium gas model, and the non - equilibrium gas model of one temperature, two temperature and three temperature

    本文採用完全氣體模型、振動激發氣體模型、平衡氣體模型、一溫度非平衡氣體模型、兩溫度非平衡氣體模型和三溫度非平衡氣體模型進行了鈍體高超聲速繞流流場的數值計算。
  9. On the mathematical simulation of non - equilibrium hypersonic flow around the flying vehicle

    關于飛行器高超聲速不平衡氣體繞流的數值模擬
  10. 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。
  11. The cell - centred finite volume algorithm, nnd finite volume algorithm and ausm + finite volume algorithm are studied for solving the euler equations, their abilities for hypersonic problem are studied especially

    本文分別對格心有限體積格式、 nnd有限體積格式和ausm +有限體積格式進行了研究，在求解euler方程的基礎上，研究了它們對跨音速以及高超聲速流場計算問題的解決能力。
  12. But the nnd algorithm can " t reach 2 - order precision, and the cell - centred finite volume algorithm is not suit to solve hypersonic problem. for the efficiency of the four - stage runge - kutta time - stepping scheme is low, and the robust is bad for the hypersonic problem, an implicit time - stepping scheme is adopted. this scheme can preserve the results precision and improve the computing efficiency sharply, and is an innovation for the time - stepping scheme of unstructured grid

    為了解決目前傳統四步龍格一庫塔時間推進效率較低、計算高超聲速流場時魯棒性較差的問題，本文改進並採用了一種隱式時間推進格式，能夠在保證精度要求的情況下有效的提高流場計算時的計算效率，對基於非結構網格的時間推進格式有了發展和創新。
  13. 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。
  14. In order to solve the complicated supersonic / hypersonic turbulence viscous flow field, a program for steady flow is built by using implicit lu - sgs method

    建立了應用隱式lu - sgs方法的三維定常流動模擬程序，可用於求解超聲速/高超聲速粘性復雜流場。
  15. Hence, analytical expressions are developed to allow for characterization of the vehicle ’ s dynamics early in the design cycle. the method involves a two - dimensional hypersonic aerodynamic analysis utilizing newtonian theory, coupled with a one - dimensional aero / thermo analysis of the flow in the engine of the vehicle

    方法中包括一個應用牛頓力學理論的二維的高超聲速空氣動力學分析以及一個一維的氣動/熱分析，後者用於模型發動機中的流體分析。
  16. Lateral jet control technology is researched in this dissertation, based on supersonic / hypersonic missile aerodynamics and lateral jet interaction ( ji ) effects associated with the attitude control solid - propellant rocket motors system in the low endoatmospheric range

    橫向噴流干擾效應研究在超聲速高超聲速導彈總體設計和精確制導技術研究領域一直佔有重要地位。本論文針對大氣層內超聲速高超聲速導彈採用姿態固體火箭發動機側噴流控制技術的一些問題進行了研究。
  17. Taking advantage of hypersonic panel method, the analysis predicts lateral jet aerodynamic interaction for a blunted body in a hypersonic flow

    將高超聲速面元法用於噴流流場計算，計算結果與試驗結果大體一致。
  18. Using axisymmetric full navier - stokes equations, the thermo - chemical nonequilibrium flow in hypersonic nozzle was simulated and the scale effects due to nonequilibrium were analysed numerically

    摘要採用軸對稱熱化學非平衡全n - s方程，數值分析了高超聲速噴管流場中非平衡引起的尺度效應。
  19. In the numerical simulation of hypersonic chemical nonequilibrium flows, species density may become negative at the beginning of calculation, chemical stiffness is the main reason that affects the calculation ' s stability and convergence

    摘要高超聲速三維化學非平衡繞流流場的數值模擬中，在計算初期容易發生組元密度出現負值的非物理現象，另外源項的剛性是影響計算穩定性和收斂速度的主要原因。
  20. The flowfield over low - drag and long - range projectile with small attack angle is numerically studied from transonic to supersonic velocity. it provides basic work for aerodynamics characteristic of this projectile and for lateral jet interaction flowfield, and it shows this projectile can decrease drag. zonal method is tried to compute flow over projectiles and results is satisfied, but computation is much slower

    系統研究了低阻遠程彈丸在小攻角狀態，低跨聲速、高跨聲速和超聲速時的非對稱繞流流場，為該彈形氣動力研究提供理論指導並為彈丸側噴流研究奠定基礎，結果顯示低阻遠程彈丸外形具有優化繞流場、減小空氣阻力的特點。
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