激波面 的英文怎麼說

中文拼音 [jībōmiàn]
激波面 英文
shock-wave surface
  • 激 : Ⅰ動詞1 （水因受到阻礙或震蕩而向上涌） swash; surge; dash 2 （冷水突然刺激身體使得病） fall ill fr...
  • 波 : Ⅰ名詞1 （波浪） wave 2 [物理學] （振動傳播的過程） wave 3 （意外變化） an unexpected turn of even...
  • 面 : Ⅰ名詞1 （頭的前部; 臉） face 2 （物體的表面） surface; top 3 （外露的一層或正面） outside; the ri...
  1. This multi - purpose optical metering system had adopted the twyman - green interferometric system as its center, containing an advanced digital wave surface interferometry and a kind of homodyne interferometer displacement testing method with nanometer - sized capacity. at the same time, many wide - applied metering technology, for example, the diffracted field ( fringe ) measurement, co - focal lens system, optical fiber sensors and 4f ( focal distance ) space filter system which can embody the chief principle of fourier optics well, were combined into it successfully. this instrument can firstly offer and show modern optical testing method in the laboratory for majors of information processing, instrument science, measuring and testing technology and automatic technology

    該多功能激光光電實驗系統以泰曼-格林干涉（ twyman - green ）光路作核心，包括先進的數字波面干涉技術和一種基於空間干涉原理的、納米解析度零差干涉儀位移測量方法，同時將多種新穎、工程實用價值高的測量技術和光路如衍射測量、共焦顯微技術、光纖傳感技術以及反映傅立葉光學基本光學原理的4f空間濾波系統也組合進去。
  2. Integrating tynman system with polarized system together, the laser interferometer is compatible for the surface with different reflectance. first, on the basis of synthesizing different interferometric microscope, the author introduced a kind of lase interferometer combining polarized interferometry and real - time phase detection algorithms. first, a kind of optical configuration is introduced, which is realized in the above interferometer

    本文在分析了國內外不同干涉顯微系統的基礎上，根據干涉顯微測量方面的需求提出了採用偏振干涉和條紋掃描方式實時檢測波面位相的激光干涉顯微系統，提出了一種可用於表面微觀輪廓及粗糙度參數測量的光學顯微干涉系統的光路，然後介紹了條紋掃描波面位相實時檢測技術以及四步移相法，並在此基礎上完成了光學系統及相關的機械結構。
  3. In this paper, high - order accurate weighted essentially non - oscillatory ( weno ) schemes are investigated and their applications in hyperbolic conservation laws are discussed. based on this, a new weno difference scheme which based on dispersion - relation - preserving relation is developed, and representative test cases with this scheme for computational aeroacoustics ( caa ) problems has been implemented and compared in order to test capability of wave capturing ; in addition, weno schemes generally do not converge at high order in the presence of contact discontinuity of euler equations, so a conservative front tracking technique coupling weno schemes and level set method to simulate the translating density profile is presented here, and numerical simulation with this technique for representative test case has been implemented and results show the desired accuracy

    本文研究了高階精度加權基本無振蕩（ weno ）格式及其在雙曲守恆律方程中的應用，在此基礎上作了兩個方面的工作：一是針對高頻聲波問題構造出一種基於保色散關系（ drp ）的weno有限差分格式，並對計算氣動聲學（ caa ）問題的代表性算例進行了大量數值實驗，比較了該格式捕捉波數的能力；另外，針對高階weno格式在處理euler方程的接觸間斷時精度有所降低的問題，研究了利用界面追蹤技術levelset方法和高階激波捕捉weno格式相結合的一種守恆追蹤方法，並且給出有代表性的密度滑移面問題的算例，得到一致高階精度的數值模擬結果。
  4. Shock tube ; conical convergent section ; detonation ; finite volume tvd scheme

    激波管收縮截面爆轟有限體積tvd格式
  5. The numerical simulation of axisymmetric two - dimensional shock tube is studied, which has a conical convergent section, and its driving gas is the hot product of hydrogen oxygen detonation. finite volume tvd scheme is adopted and the mesh is local orthogonal. the primitive equations are euler s equations of multi - component flow. the new method of eliminating numerical oscillation at the interface of two materials is extended to two dimensions. the mechanical character of this shock tube is analyzed

    對由前向爆轟產生驅動氣體並具有局部錐形收縮截面的軸對稱激波管利用兩相常比熱完全氣體的歐拉方程組和有限體積tvd格式在局部正交的網格上進行了二維數值模擬。將消除兩種介質界面處數值振蕩的新方法成功地推廣到二維情況。分析了該激波管的力學特性。
  6. Principal conclusions were drawn as the following : the non compatibility of pressure or velocity of the gas on both sides of the contact surface is the cause of the formation of shock wave ; the heating effect of reflective shock wave to driving gas during charging or exhausting process is the internal mechanism of peak oscillating effect, and all the factors that influence the formation and the running of the shock wave will influence the peak oscillating frequency, cooling effect

    主要結論如下：熱分離機內激波形成的原因是射氣瞬間接觸面兩側壓力和速度不相容；峰值振蕩效應的內在機制為反射激波對充氣階段的驅動氣或低溫排氣的加熱，凡是影響激波形成及運動的因素都將對峰值振蕩頻率、冷效應及熱效應產生影響；當充、排氣時間比為0 . 1763時，最佳射流激勵頻率出現在高階峰值振蕩頻率上。
  7. A preliminary analysis shows that the east - west asymmetry in the heliospheric equatorial plane is mainly attributed to the spiral structure of the interplanetary magnetic field

    初步分析表明，行星際磁場的螺旋結構是產生日球赤道面內雙重激波對結構東西不對稱性的主要原因。
  8. Based on an engineering background, through numerical simulation of the flow field in the hp turbine of the energy efficient engine ( e3 ), the article research the unsteady flow in a transonic turbine stage, the unsteady phenomena in the stage include the shockwave, wake, shedding vortex, endwall vortex, passage vortex and leakage vortex, etc. there are two shockwaves generated on the vane the tailing edge, one on suction side is named moving shockwave, and name another on pressure side steady shockwave

    本文首先對于研究的意義和國內外研究的現狀做了簡要的介紹，再從某工程背景出發，通過對e3發動機高壓渦輪內流場的數值模擬，研究了干涉的周期性的問題，以及渦輪級內常見的非定常現象：激波、尾跡、脫落渦、根腳渦、通道渦、漏流渦。導向器尾緣會出現兩道激波，在吸力面的激波可稱為「運動」激波，壓力面的激波可稱為「定常」激波。
  9. All of these reveal the further properties of the wave propagating in one - dimensional elastic continuum. on phase plane, the qualitative analysis are made, which exhibits four kinds of orbits : the heteroclinic orbit of burgers equation, the homoclinic orbit of k - dv equation, and saddle - foci heteroclinic orbit or saddle - joint heteroclinic orbit of kdv - burgers equation

    說明burgers方程在相平面上有相應于激波解的異宿軌道; k ~ dv方程有相應于孤波解的同宿軌道: kdv一buegers方程有相應于振蕩孤波解的鞍一焦異宿軌道和相應于激波解的鞍一結異宿軌道。
  10. 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。
  11. A multifunctional laser interferometer which can be used to measure the three dimension microcosmic profile and roughness of optical component is introduced in this dissertation. it covers microscopy, polarized interferometry and real - time phase detection algorithms

    本文提出並實現了一種由光學顯微系統、偏振干涉技術和條紋掃描波面位相實時檢測技術相結合，集三維輪廓測量和粗糙度測量為一體的多功能激光數字化干涉顯微系統。
  12. The control - equations were solved with upwind tvd algorithm and elemental chemical reaction model, with the point - implicit used to overcome the numerical stiffness of chemical reaction source term

    數值結果顯示，當爆轟波平掠過惰性氣體界面時，形成了爆轟波、界面、透射激波以及稀疏波相互作用的現象。
  13. More attentions are taken to the applications of the interferometer for the quantificational and real - time measurements in the following aspects : the laser ' s wavefront, the homogeneity of laser bar, angle deviation of flatness optical components, and surface roughness

    重點研究了數字式波面干涉儀的應用，定量、實時測量了激光波前質量、激光棒波前畸變、利用波面計算錐體棱鏡角度、表面粗糙度等。
  14. Numerical simulations were done to show the distortion of the wavefront and the interference pattern under several kinds of typical plasma density distributions. the ray path in plasma was calculated by the numerical solution of the vector equation of light ray, when the plasma density was closing to the critical electron density of the laser frequency. through the simulations, the factors that influence the measurement were found out under different density distributions and shapes of plasma

    在此基礎上，採用數值模擬的方法，計算了在幾種典型的等離子體密度分佈下，激光波面的變化和產生的干涉圖樣；並用光線矢量微分方程的數值解法計算了當等離子體密度接近光頻臨界電子密度時，光線在等離子體中的傳播路徑，從中掌握了在不同的等離子體密度和形狀下，進行干涉測量所應估計到的因素。
  15. Taking m6 wing and f4 wing - body configuration as computational examples, some results by solving euler and n - s equations are presented. compared with the results of wind tunnel experiment, the results of n - s solver are much better than those of euler solver, and the upwind scheme is better than the central scheme in catching shock wave

    本文以m6機翼和f4翼身組合體為算例，對euler方程和n - s方程的計算結果進行了比較，從算例上可以看出， n - s方程的計算結果更接近實驗值；對中心差分格式和迎風格式的比較，可以看出，在激波的捕捉方面，迎風格式比中心差分格式更精確。
  16. And then, in the simulation of three - dimensional, the application of o - type grid and hybrid grid are used in two relatively complicated structures make the total amounts of grids and the time of grid generation reduced greatly. moreover the hexahedron grids are placed in most areas to provide higher precision. through the comparison between the results of two - dimensional and three - dimensional simulation, we knew two - dimensional calculating is not adequate

    本文用簡單、方便的二維模型作為數值計算的起點，使用耦合隱式演算法以及先進的v2f湍流模型進行求解，成功地捕捉到了激波，觀察到主氣流從壁面的分離、切換、再附壁等現象，並對計算結果進行了細致的分析，得出一些有意義的結論；在此基礎上，本文在國內外首次對超音速射流雙穩閥的三維流場進行了計算。
  17. Adaptive grid techniques through a variational approach are applied to two shock problems with exact solutions. more grid points are redistributed in the shock regions in response to numerical solution and thus the shock can be captured successfully. the results show the techniques have excellent qualities in improving accuracy of numerical solution and reducing cpu time

    利用變分原理的自適應網格技術被應用到兩個有解析解的激波問題上，它能根據問題的求解，在解的大梯度區自動加密網格，從而非常成功地算出了激波。通過分析發現自適應網格技術在提高精度減少運行時間方面顯示了優良的性能。
  18. The complex vortex system structure and shock wave system structure inside this rotor is obtained. wall flow patterns on the blade surface and hub surface are found out. the complex vortex system structure, such as horseshoe vortex, passage vortex, corner vortex and trailing vortex, and the interaction with shock wave system are researched. especially, the character of the tip clearance flow inside the rotor passage is revealed, and the interaction between shock wave and tip clearance flow near blade tip and the evolution of tip clearance flow are considered

    給出了葉片表面及輪轂面上的壁面流型，分析並揭示了轉子葉道內的馬蹄渦、通道渦、角渦、尾渦等復雜渦系及其與激波的相互干涉；特別是，分析並揭示了轉子葉道內頂隙射流的特點，得到了頂隙附近激波與泄漏流動的干涉形態及泄漏流動的發展，並著重給出了其與激波的干涉形態。
  19. The velocity distributions, the relative mach number distributions and the flow trace distributions are visualized, and the reasons, which cause bad aerodynamic losses and make the flowfield complicated, are analyzed, including wake, secondary flow, separated flow and the interaction between shock and boundary layer

    顯示壓氣機內的速度場、相對馬赫數分佈及流動跡線分佈等，並分析造成嚴重損失及使流場趨于復雜紊亂的原因，包括尾跡、二次流、分離流及激波/附面層干擾等現象。
  20. All the improvements included the modifications on the sound velocity, characteristic mach number and the mach number at the grid interface. several 2d flow fields which had shock, shear flow, rarefaction wave, or turbulent boundary layer and the combination of them were computed

    該格式改進了聲速、特徵馬赫數的處理方式，對網格界面馬赫數進行了修正，並求解了含有脫體激波、斜激波、剪切流、膨脹扇、及湍流附面層等流動特徵的復雜流動。
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