wind-tunnel experiment 中文意思是什麼

wind-tunnel experiment 解釋
風洞實驗
  • wind : n 1 風；大風，暴風；氣流；【機械工程】壓縮空氣。2 【航海】上風；風向；〈古語〉〈pl 〉方向。3 氣息...
  • 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...
  • experiment : n 實驗；試驗；嘗試 （of） a scientific experiment 科學試驗，科學儀器設備。 a new experiment in ed...
  1. Second, according to field investigation and wind - tunnel experiment, some scholar s advanced that barchan dunes often appear in dynamic equilibrium shapes when th ey move along the direction perpendi cular to the dune ridge under the influence of unimodle sand - moving wind

    風成沙的紅化和圓度特徵不宜作為判別其氣候意義的診斷性標志，應當結合動植物化石及石英砂顯微結構等線索來確定。
  2. This paper adopts linear interpolation to deal with data of wind tunnel experiment for sample uav and realizes modeling and simulation of the sample uav with c language in common aerodynamics and moment coefficient

    本文採用線性插值處理樣例無人機風洞試驗數據，採用正常情況下的氣動力及力矩系數數學模型，並用c語言實現樣例無人機建模與模擬。
  3. Fluid experiment ; buff body aerodynamics ; wind engineering ; wind loading on buildings and structures ; modeling wind in an atmospheric boundary wind tunnel ; pedestrian - level wind environment ; wind effects on the efficiency of air - cooled condenser in a large power plant

    實驗流體力學，鈍體空氣動力學，風工程， 、建築物和結構物的風荷載研究，大氣邊界層風洞模擬，行人高度風環境，大型電站空冷系統風效應風洞模擬。
  4. It is for the first time in domestic wind tunnel experiment that to adopt high voltage transducer to rebuild adjusting system of flow field of large - scale wind tunnel

    採用高壓變頻器來改造大型風洞的流場調節系統，在國內風洞業界還是首次。
  5. Low speed wind tunnel experiment requires strict of the wind speed, which requires a wild range of wind speed, high precision, and quick adjustment

    低速風洞實驗要求對實驗段的風速有嚴格的控制，要求風速調節范圍寬，精度指標高，調節速度快。
  6. 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。
  7. In this paper, the wind loading time history of the truss structure is simulated according to the data of wind tunnel experiment and pulsating wind spectrum, and the transient dynamic analysis is used on the fem

    本文依據風洞試驗數據模擬了靜風壓的空間分佈，依據脈動風譜模擬了網架結構的風荷載時程，並對有限元模型進行了有限元瞬態動力學時程分析。
  8. Wind tunnel experiment on the model of the chinese national grand theatre

    中國國家大劇院模型風荷載風洞實驗
  9. With the development of global economy and intensifying competition in aviation industry, which have caused transform in wind tunnel experiment field. new tide of wind tunnel experiment comes out. to be on top in this area, the occident has invested a mint of capital to update and rebuild their facility of wind tunnel, to adjust working pattern, to improve efficiency and to develop new experimental technology

    隨著經濟全球化的發展，世界航空工業的競爭加劇，導致了風洞試驗領域的變革，風洞試驗業也呈現出新的發展趨勢，為了贏得在新世紀航空領域的領先地位，歐、美都投入巨資對風洞設備更新改造，調整運行模式，提高效率，發展新的試驗技術。
  10. The main results of the wind tunnel experiment on the 1 200 model of the chinese national grand theatre were introduced. at first, the wind pressure distributions of its semi - ellipsoidal surface in an atmospheric boundary layer flow were simulated, and the effect of the surface roughness was researched. the results indicated a reasonable regularity of its wind loading in various wind directions. on the problem of the environmental influence, it demonstrated that there existed a great effect for the pressure distribution of the great theatre when the grand hall is at east

    介紹中國國家大劇院模型表面風荷載的風洞實驗結果。首先對它的半橢球表面在大氣邊界層中的風壓分佈及增加表面粗糙度的影響進行研究，實驗結果表明在不同風向下它的風荷載具有很好的規律性。有環境影響的對比實驗結果表明人民大會堂對大劇院的風荷載有較大的影響。
  11. The application of plc and human machine interface and inverter in the speed - adjust system of the low speed wind tunnel experiment

    與人機界面在低速風洞調速系統上的應用
  12. Physical modeling of atmospheric boundary layer wind tunnel experiment

    大氣邊界層風洞實驗的物理模型
  13. The main study method of wind engineering of structures is wind tunnel experiment

    當前，風洞試驗是研究風工程的主要手段。
  14. Wind tunnel experiment on the impacts of polyacrylamide on wind erosion of loosen soil materials

    防治鬆散擾動沙土風蝕效果的風洞試驗研究
  15. The viscous flow around m6 wing and f4 wing - body configuration are simulated and compared with the results of wind tunnel experiment

    為了驗證方法和程序的正確性，論文中對m6機翼和f4翼身組合體的流場進行了數值模擬，並與試驗結果進行了對比。
  16. The experiment result showed that motor designed by the method satisfy the needs of wind tunnel experiment, have high performance with low price and intensive engineering application value

    實驗結果表明，使用該方法設計的電機滿足了風洞實驗要求，具有較高的性價比和較強的工程應用價值。
  17. In addition, the paper introduces the seismic design of open top floor, the design of steel cover, the test of static bearing capacity of pile and the test of wind tunnel experiment

    此外，本文還介紹了空曠頂層的抗震設計:鋼結構屋蓋的結構設計;介紹了樁基靜載試驗和風洞試驗的概況及其試驗成果。
  18. With a numerical code and a computing software, the aerodynamics characteristics of the shapes are discussed. the feature of the waverider configurations is proved by this work and the analysis of the off - design aerodynamics characteristics is also emphasized in this study. finally, an experimental model is developed for a wind tunnel experiment to demonstrating the numerical analysis

    採用了軟體和數值程序相結合的方式對初步設計的乘波構形流場進行數值分析，驗證了乘波外形的流場和氣動特性，討論了乘波構形氣動特性隨外形設計參數的變化，對外形在非設計狀態下的氣動特性進行了重點的討論，得到了氣動特性變化的一些基本規律。
  19. Also longitudinal aerodynamic characteristics of missile are investigated. the traditional dependence on wind tunnel experiment is changed greatly : firstly, the aerodynamic characteristics of missiles with complex configuration are solved satisfactorily, especially integral rocket - ramjet missile ; secondly, feasibility of n - s equation to numerical simulation of inner and outer fiowfield of missile with complex configuration is discussed

    （ 3 ）採用n - s方程方法數值模擬某型整體式沖壓發動機導彈的全彈內外流場，研究了導彈的縱向氣動特性，改變了過去依賴于地面風洞試驗結果的傳統做法。
  20. First, being based upon kalman filter, extended kalman filter formulas was established ; second, with using extended kalman filter in non - linear dynamics system maximum likelihood identification method, the self - contained formulas of estimating parameter was established ; third, according to the air layout of the missle, the aerodynamic parameters identification calculating model was gained, with applying to the non - linear dynamics system maximum likelihood identification method ; finally, with using the calculating model, the aerodynamic parameters were gained. the results which were gained from the calulating model were almost consistent with which were gained from the wind tunnel experiment. thus, it was viable to use the method to estimate the aerodynamic parameters

    首先，以卡爾曼濾波為基礎，將其推廣于非線性動力學系統，建立了廣義卡爾曼濾波算式；其次，把廣義卡爾曼濾波算式應用於非線性動力學系統最大似然演算法和非線性動力學系統最大似然遞推演算法中，建立了各自的參數估計完備算式；再其次，以所建立的傾斜穩定導彈空間運動數學模型為基礎，根據該導彈的氣動布局，推導並建立了該導彈空間運動數學模型，將最大似然遞推演算法應用其中，建立了導彈氣動力參數辨識的數學模型；最後，利用該模型，估算出了氣動力參數，所得結果與風洞實驗數據基本吻合，從而認為採用此方法是可行的。
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