翼型外形 的英文怎麼說
中文拼音 [yìxíngwàixíng]
翼型外形
英文
airfoil contour-
In this paper, some flows around naca 0012 aerofoil, m6 wing and two different blunt vehicles are simulated, the results show that the present algorithm possesses good characteristics and capability for normal mach number and for hypersonic of simple configurations
通過對naca0012翼型、 m6機翼、鈍頭以及雙鈍錐?柱體的算例驗證，本文能很好的解決一般馬赫數問題，能夠很好的求解簡單外形的高超聲速問題，對于復雜外形飛行器還需要進一步進行研究驗證。This paper has mainly made a research on the aerodynamic configuration design of " w " tailless aircraft and the design idea has been presented here. according to the configuration design requirement of certain uav, aerodynamic configuration design has been carried out and two configuration projects are given out at last : forward - swept wing tailless configuration and " w " tailless configuration. the longitudinal and lateral aerodynamic characteristics are obtained by using two aided soft : ug to build up geometrical models and mgaero to calculate flow field
本文研究了「 w 」型無尾布局的氣動外形設計，闡述了該布局的氣動設計思想，根據型無人機的總體設計技術指標，進行了氣動外形設計，提出了兩種氣動布局方案：前掠翼無尾氣動布局和「 w 」型無尾氣動布局，利用ug建模軟體和mgaero氣動分析計算軟體計算了兩種布局的縱、橫向氣動性能，分析了前掠翼前緣掠角和翼身融合對氣動性能的影響，計算結果表明， 「 w 」型氣動布局的設計思想是正確的，所設計的「 w 」型無尾氣動布局方案的氣動性能優越，超過了總體設計技術指標。Many test cases are calculated to verify the above study. the cases are either real or standard testing models, including multi - element airfoil, wing - body configuration, cone / cylinder missile model and 3 - d high - lift systems, etc. the results of present calculation are in good agreement with experiment data, and show flexibility and accuracy of the approaches. base on the cartesian grids, this thesis has targeted the development and integration of many algorithms and techniques such as adaptive refinement, omni - tree data structure, hybrid grid method, etc. an analysis software and research methods are designed and developed for the steady - unsteady and viscous - inviscid flow complex systems and configuration
7 .運用上述研究成果和結論，進行了大量算例的實驗驗證，外形范圍包括多種標模與型號，涉及多段翼型、 m6機翼、細長體模型、翼身組合體、兩段機翼增升標模、帶縫翼和襟翼的三段增升翼身組合體等復雜外形，計算結果均與實驗吻合良好，充分說明了本文發展的各種演算法、流場求解、網格生成方法的正確性和魯棒性。In spite of these advantages, we should concentrate on how to extend the representation of modes, how to apply to unstructured grids, etc. and when combining pod and saa, it is necessary to know how to represent the shape and how to control the range of seeking and iteration number
但在研究的過程中，我們發現正交分解方法也存在如下問題:如何增強基模態的表達能力，如何將該方法應用於非結構網格的計算等。在利用模擬退火演算法結合解算器進行翼型反設計時，則需要考慮如何表達幾何外形形狀，怎樣控制搜索范圍以及如何減小搜索次數等實際問題。On the assumption of ignoring the distortion of thickness, this paper determines the rough shape by the geometric modeling method of equal area developing using mixed mesh cell of triangle and quadrangle for the first time, presents the equal area developing arithmetic of quadrangle - triangle. on the virtual geometric symmetry axis, we puts forward the method of determining the developed coordinate of the point on the base band in the development of using regular quadrangle cell, determines the developed shape of internal structure in plane utilizing point - to - point mapping theory. furthermore, we realize the approximate developing of undeveloped - irregular boundary surface using a few triangle cells
本文結合型號研製中小曲率機翼整體壁板類零件坯料展開課題，基於板料厚向變形忽略不計的先驗假設，首創混合四邊形-三角形網格等面積展開的幾何模擬法確定壁板類零件毛坯外形，給出了混合四邊形-三角形網格等面積展開演算法；提出了虛擬分割線的概念，採用虛擬幾何對稱軸，給出了規整四邊形單元展開基帶上結點的計算方法；採用映射原理和求交演算法確定了壁板內部結構信息的展開定位。A technology for designing a dishing axial - symmetric unmanned helicopter that based on a coaxial rotor system shrouded by a toroidal shell is studied in this thesis
本文研究碟形軸對稱無人直升機的總體設計技術，這種特型的無人直升機是將一副共軸式旋翼置於涵道中，外形為碟狀。Independent packaging style : sanitary napkin after folding wings is stuck with outer package film and then three - folded. products are sealed with adhesive tape and become into square small package
獨立包裝型式：合翼貼紙后的衛生巾膠貼外包膜后直接三折包合，易撕帶封口，形成方片狀小包。Secondly, the static aeroelastic problems and jig - shape design, as a kind of multi - disciplinary design optimization ( mdo ), are investigated for sweep wing and super - critical wing. numerical results are in good agreement with other reference data. the method and the program presented in this paper are verified
分別以某后掠機翼和超臨界機翼為算例，對機翼的靜氣動彈性問題以及基於靜氣動彈性的型架外形優化設計和飛行姿態確定進行研究，計算結果和有關文獻的結果進行了比較，吻合很好。The effect of the number of grid, liquid water content ( lwc ), median volumetric diameter ( mvd ) and ice layer time step on ultimate ice shape is analyzed, the aerodynamic characteristics of the iced airfoil is analyzed simply, too
分析了網格數、空氣液態水含量、水滴當量體積直徑和冰層時間步長對模擬冰形的影響，此外還對結冰翼型的氣動特性進行了簡要的分析。分享友人