hypersonic tunnel 中文意思是什麼

hypersonic tunnel 解釋
高超音速風洞
  • hypersonic : adj. 高超音速的〈指超音速五倍以上者〉。
  • tunnel : n 隧道；地道；坑道；管道，煙道，風洞；【礦物】石巷，平峒。 tunnel warfare 地道戰。vt （〈英國〉 l...
  1. 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。
  2. A hypersonic pulse tunnel is designed in this paper, which has multiple running modes based on gun tunnel and shock tube theory

    本文設計了一座具有多種運行方式的高超聲速大型脈沖風洞，該風洞可以採用炮風洞和激波管兩種運行方式。
  3. The results show that to design a supersonic / hypersonic nozzle of wind tunnel must consider the effect of variable specific heat, which gives reference to nozzle and wind tunnel design

    考慮這一因素后，噴管出口馬赫數接近設計馬赫數，其設計精度有較大提高。本方法可為超音速高超聲速噴管設計和反設計提供參考。
  4. This paper presents the development and preliminary application works of an automatic strain gauge balance static calibration system in ecs for 1m hypersonic wind tunnel of cardc

    本文論述了cardc超高速空氣動力研究所1m高超聲速風洞配套的新型全自動六分量應變天平地軸系（ ecs ）校準系統的研製和初步應用研究工作。
  5. It is no effect on a sidewall compression inlet ' s starting characteristics while a starting sidewall compression inlet is moved cowl to increase interior contraction ratio appropriately. back pressure effect on characteristics of self - starting for hypersonic sidewall compression inlet is tested in mach 3. 85 wind tunnel. the hypersonic sidewall compression inlet with interior contraction ratio 1. 24 can self - start. unstart hypersonic sidewall compression inlet caused by high back pressure can self - start by moving cowl to decrease interior contraction ratio

    最後，實驗研究了反壓對側壓式進氣道自起動特性的影響，內收縮比1 . 24的側壓式進氣道可以實現自起動並且實驗驗證了由於反壓過高而不起動的側壓式進氣道，通過移動唇口板以減小內收縮比可以實現側壓式進氣道的自起動。
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