hypersonic model 中文意思是什麼

hypersonic model 解釋
高超音速模型
  • hypersonic : adj. 高超音速的〈指超音速五倍以上者〉。
  • model : n 1 模型，雛型；原型；設計圖；模範；（畫家、雕刻家的）模特兒；樣板。2 典型，模範。3 （女服裝店僱...
  1. The design point of the designed forebody / inlet is flight mach number m = 6 and flight attitude h = 25km. the three - ramp, mixed external and internal compression hypersonic / inlet is chosen as representative geometry to be designed. nine types of hypersonic / inlet model with difference forebody length and total turning angle are obtained that the incidence angle of the first ramp and height of isolator are given

    根據飛行任務要求，以飛行馬赫數6 ，飛行高度25km為設計點，給定前體預壓縮角、隔離段高度，對具有不同前體長度和不同總壓縮轉角的帶隔離段的前體進氣道進行了設計。
  2. 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。
  3. Several non - linear phenomena are also analyzed. by using uncoupled thermal - structure analyzing method, with the consideration the additional stiffness caused by thermal stress, the finite element model for thermal - vibration analysis is obtained and two typical hypersonic wing structures are computed

    運用非耦合熱-結構分析方法，考慮熱應力引起的附加剛度，得到熱環境下的結構分析的有限元模型，並計算了兩種典型結構的高超音速翼面熱結構。
  4. Scramjet inlet is of great importance in the hypersonic airbreathing propulsion system and plays significant role in the realization of hypersonic flight. full 3 - dimensinal n - s equations are solved by using finite volume method, second - order harten - tvd spatial scheme, and algebraic baldwin - lomax turbulence model

    本文基於favre質量加權平均的三維navier - stokes方程，採用有限體積法、二階的tvd格式進行流場求解，並使用了bladwin - lomax代數湍流模型。
  5. 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。
分享友人
分享到 Line

分享到臉書