激波 的英文怎麼說

中文拼音 [jībō]
激波 英文
[物理學] blast; shock wave
  • 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...
  1. Hot firings show that the frequency of the oscillating shock is close to the acoustic frequency.

    熱試結果表明，振蕩激波的頻率與聲頻相近。
  2. Asymptotic stability of viscous shock profiles for one - dimensional viscous conservation laws with boundary effect

    一維粘性守恆律初邊值問題粘性激波解的漸近穩定性
  3. The final part of this section deals with the effects of shock waves on the breakup of liquid jets and drops.

    本節最後一部分涉及的是激波對液體射流和液滴破裂的影響。
  4. The pressure behind this shock wave drives an inward - moving shock wave that heats the ejecta, seen as the aqua cloud

    激波后的壓力驅使內行激波加熱物質，也就是圖中淺綠色的雲團。
  5. The expanding ejecta drive an outward - moving shock wave that races ahead of the ejecta into the interstellar gas ( bright outer rim )

    膨脹的拋出物驅動著外行激波，領先於拋出物沖入星際氣體（明亮的外緣） 。
  6. The clear separation of the shocked matter and the heated ejecta in the chandra image allowed astronomers to determine the mass and composition of the ejecta

    在錢德拉的照片上，激波擾過的物質與被加熱的拋出物之間明顯的分隔讓天文學家可以定出拋出物的質量與組分。
  7. Shock ejection from a tube and propagation in forest belt

    激波噴出過程和在林帶中的傳播
  8. With account for the effect of temperature and shock - boundary layer interaction, the forebody / inlet with plane lip and wedge lip are designed by using the design methods of constant shock wave intensity and constant shock wave angle. in the design, the incidence angle of the first ramp, height of isolator, length of forebody and total turning angle of the designed forebody / inlet models are given

    另外，根據優選結果，給定前體長度、前體預壓縮楔角、總壓縮轉角及隔離段高度，分別用等激波強度和等激波角度的方法設計了唇口平直和唇口帶楔角的前體進氣道。
  9. 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。
  10. Hypersonic shock tube

    高超聲速激波管
  11. A simple limiter similar to the one of earth and jespersen is presented to eliminate unphysical oscillations near discontinuities

    發展了一種簡單高效的通量限制器抑制激波處的非物理振蕩。
  12. The fixed expansion points of the general shroud allow a better definition of local shock locations than on ogive type shrouds.

    一般外殼的固定膨脹點能比蛋形外殼更好地限定局部激波的位置。
  13. And finally, with hllc and lax - friedrichs type approximate riemann solver for discretising conservative equations and a nonconservative equation, a simple accurate and fully eulerian numerical method is presented. compared with the numerical results of hll scheme, the hllc scheme has a high resolution for shock waves and avoiding the nonphysical oscillation of the hll scheme

    最後用lax ? friedrichs格式及hllc格式作為通量函數對守恆一維euler型方程組進行了離散，並將數值模擬結果和saurel的hll格式模擬結果進行了比較，發現：在兩相流數值模擬過程中，相對來說hllc格式對激波的解析度最高，結果最穩定，避免了hll格式在間斷處的非物理性數值振蕩。
  14. Shock front thickness

    激波前沿厚度
  15. The hottest gas ( higher - energy x - rays, colored blue ) is located primarily in the regions directly behind the shock front

    最熱的氣體（高能x射線，以藍色表示）主要位於激波波前的後方。
  16. In order to verify the prediction efficiency, 27 interplanetary shock events from january 1979 to june 1982 and 68 interplanetary shock events from february 1997 to january 2000 are used for testing. comparing the results of our disturbance model to those obtained by stoa and ispm, we find that our disturbance model is as good as the other two models, and in some cases even better

    為印證擾動傳播模型的適用性，利用79年到82年間的27個激波事件，以及97年2月到2000年1月間的68個激波事件，對激波到達地球軌道附近的傳播時間進行了預測，並將結果與目前流行的行星際激波事件到達地球軌道時間的stoa和ispm預報模型所得結果進行了比較。
  17. Meanwhile, the spectrum is also related to the shock wave velocity

    光譜的結構特徵也依賴于激波的速度。
  18. Numerical simulation of windward vortex shocks about supersonic slender bodies at high angles of attack

    超聲速大攻角旋成體迎風激波數值模擬
  19. 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。
  20. The results show that it is the numerical method of high analyzable degree for the hybrid tvd scheme combinated with fvm, and the scheme is not only sufficiently accurate and nonoscillatory, but also capable of treating automatically hydraulic jump

    算例驗證表明：應用組合型tvd ? muscl格式配合有限體積法是一種高解析度的數值方法，且tvd ? muscl格式對于自動捕捉激波和抑制間斷附近的數值解波動十分有效，它對間斷具有高解析度。
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