shock configuration 中文意思是什麼

shock configuration 解釋
激波形態及分佈
  • shock : n 1 沖突；沖撞；沖擊；突擊。2 震動；沖動；激動。3 感動；憤慨；驚愕；震驚。4 地震。5 【醫學】休克...
  • configuration : n. 1. 結構；構造；圓形，外形。2. 組合，布置；配置。3. 地形；【天文學】（行星等的）相對位置，方位；【化學】（分子中原子的）組態，排列；【物理學】位形；組態。
  1. 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。
  2. 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。
  3. 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。
  4. It can be placed without vibration to flow level and degas, more applicable to complex configuration, thin space or where there are densely distributed anchors, better thermal shock resistance than vibration castables with the same material system

    施工不需振動即可自流平和脫氣，易於施工形狀復雜、狹窄和有密集錨固件的部位，抗熱震性優于同材質的振動澆注料。
  5. The ratio of mach number between lateral jet and free flow induce intensity degree of jet interaction. it has no obvious difference between two interactions with two types of nozzle exit configuration, rectangle and ellipse. the shock in front of jet results in increase of shock resistance and the jet ejection causes increase of base resistance

    研究表明，側噴流與來流馬赫數之比是影響繞流場的重要因素，該值越大則側噴干擾越強烈，矩形和橢圓形兩種側噴口形狀對側噴流場干擾波系的影響並不明顯。
  6. The configuration of the diffuser should be designed as a channel to allow the main flow pass through a shock train

    擴壓段的形狀應設計成能使主氣流通過系列斜激波串減速的通道。
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