hypersonic flow 中文意思是什麼

hypersonic flow 解釋
超空間
  • hypersonic : adj. 高超音速的〈指超音速五倍以上者〉。
  • flow : vi 1 流，流動。2 （血液等）流通，循環。3 流過；川流不息；（時間）飛逝；（言語等）流暢。4 （衣服、...
  1. 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
  2. ( 2 ) to evaluate the effects of a reaction control jet on the aerodynamic performance of a missile operating at supersonic / hypersonic flight condition, the single and two attitude jet - interaction flow between a lateral jet and the external flow has been analyzed by detailed numerical simulation

    （ 2 ）分別計算了單噴流和雙噴流干擾流場。詳細分析了流場結構和彈體表面壓力分佈特性，獲得了一些有實用價值的結果。
  3. 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。
  4. 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
  5. 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。
  6. Preliminary observation on ultraviolet emission spectra in non - equilibrium 2 - d hypersonic blunt body shock layer flow

    二維高超聲速鈍體激波層紫外輻射的實驗觀察
  7. The software fluent was employed and the two - dimensional flow field and performance parameters of four hypersonic / inlet models at design and off - design condition are obtained

    採用fluent軟體對所設計的進氣道設計點和非設計點二維流場和性能進行了數值模擬。
  8. Using the engineering methods of supersonic and hypersonic flow or local piston theory developed in this paper to compute unsteady aerodynamic loads, and coupling structural equations, the supersonic or hypersonic aeroelasticity with a typical servo system under thermal environment is simulated in time - domain

    運用超音速、高超音速氣動力工程計算方法和本文發展的當地流活塞理論計算非定常氣動力，耦合結構運動方程，實現了熱環境中帶有伺服機構的氣動彈性的時域模擬。
  9. 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。
  10. 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。
  11. 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。
  12. In this paper, a three - dimensional ( 3d ) program for the three - dimensional reactive flow fields of complicated geometric nozzle, which governed by the compressible full navier - stokes equations with realizable k - s turbulent model, has been upbuilt by using full implicit couple arithmetic and fvm ( finite volume method ) based on understanding and assimilation of a two - dimensional program group of cr ( chamber - radon ). the new program fulfils the urgent need of numerical tools for simulating three - dimensional reactive flow - fields of hylte ( hypersonic low temperature ) and other latest nozzles, for which cr is out of action in simulation, and can be applied to simulate other chemical laser system, such as chemical oxygen iodine laser ( coil ), overtone fluoride hydrogen, all - gas iodine laser, and so on. furthermore, some related topics about nozzles design and engineer ing also have been discussed

    本文在二維cr （ chamber ? radon ）程序研究的基礎上，採用有限體積方法和完全隱式的耦合演算法，通過求解帶realizablek -兩方程湍流模型的多組分、有反應的三維完全納維埃?斯托克斯（ n ? s ）控制方程，建立了一套能夠對復雜形狀的三維噴管和光腔進行數值模擬的三維程序，解決了連續波df hf化學激光器增益發生器設計缺乏三維數值模擬工具的問題，並用該工具解決了cr程序無法實現的hylte等復雜三維噴管流場的理論模擬問題。
  13. 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。
  14. The improved ausmwk scheme was extended on the three - dimensional flow field. three complicated 3d flow which included a supersonic flow at the comer of the intersecting wedges, a hypersonic flow in the lifting - body configuration and a flow in the rotating frame were numerically simulated by using ausmwk. results showed that the improved scheme could predict the complex turbulent flow more effectively than the original one.

    通過與實驗數據的比較，數值結果詳細、準確地揭示了這幾個復雜流場的流動現象，證實了ausmwk格式的改進是成功的，發展的ausmwk格式繼承了ausm +格式優點，計算處理問題能力增強，可以有效地應用於亞聲、跨聲和高超聲流動的工程實際問題中。
  15. Through the paper " s study, the cell - centred finite volume algorithm and the 2 - order ausm + finite volume algorithm can solve the subsonic flow problem well ; the nnd finite volume algorithm and 2 - order ausm + finite volume algorithm can solve the hypersonic flow problem well

    研究表明，對于跨音速問題，格心以及二階ausm +格式解決的很好；對于高超聲速問題， nnd和ausm +格式解決的很好。
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