翼前緣 的英文怎麼說

中文拼音 [yìqiányuán]
翼前緣 英文
nose of wing
  • 翼 : Ⅰ名詞1 （翅膀） the wing of a bird 2 （像翅膀的東西） the wing of an aeroplane etc : 鼻翼 wing of...
  • 前 : Ⅰ名詞1 （在正面的） front 2 （次序在先的） first; top 3 （過去的; 較早的） ago; before; preceding...
  • 緣 : Ⅰ名詞1 （緣故） reason 2 （緣分） predestined relationship 3 （邊） edge; fringe; brink Ⅱ動詞（攀...
  1. Fracture analysis of joint pole for front edge wing on boeing 735 - 500 plane

    500飛機前緣襟翼操縱連桿斷裂分析
  2. The tiles are backed by a high-temperature-resistant material on the nose and leading edges of the wings.

    這些面磚敷貼在用耐高溫材料製成的機頭和機翼前緣。
  3. In addition to a longer nose, aerodynamic modifications feature kfir - style small nose side - strakes to prevent yaw departure at high aoa, a pair of fixed delta canards on the upper parts of the air intakes, dog - tooth outboard leading - edge extensions, and short fences replacing leading - edge slots

    除了一個加長的機鼻外，氣動布局的修改包括：在機鼻兩則裝上可以防止在高攻角下脫離偏航的「幼獅」式小邊條，一對固定在進氣道的三角鴨翼，鋸齒型外翼前緣，和代替前緣翼槽的短翼刀。
  4. A handling party rushed forward and grabbed hold of special toggles on the trailing edges of the wings.

    一群地勤人員沖向前去，抓住了機翼后緣上的特殊套環。
  5. Numerical investigation of the effects of different leading - edge profiles on vortical flows over a double - delta wing

    尖頂襟翼長度對三角翼前緣渦破裂的影響
  6. The effects of trailing edge jets on the vortex breakdown of a delta wing

    后緣噴流對三角翼前緣渦的影響
  7. Effect of apex flap length on leading edge vortex breakdown over delta wings

    三角翼前緣渦破裂形式及特性研究
  8. Experimental analysis on oscillations of vortex breakdown location over delta wing

    三角翼前緣渦破裂點脈動的實驗分析
  9. The effects of vectored jet on leading edge vortex breakdown of 65 176 ; delta wing

    矢量噴流對65 176 ;三角翼前緣渦破裂的影響
  10. Effect of the apex flap on the leading edge vortex breakdown over a 70 176 ; delta wing

    尖頂襟翼對70 176 ;三角翼前緣渦破裂的影響
  11. 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。
  12. Abstract : the effects of airfoil geometric parameters on wing " s spacial and polarized scattering characteristics have been systematically revealed. the results of the study indicated that the calculating value of diffraction from trailing edge by using the formula of the straight wedge is very far from experimental results for vertical polarization, and the contribution of thickness of the trailing edge to scattering must be considered in the calculation. the scattering peak of leading edge depends only on radius of airfoil for horizontal polarization. but for vertical polarization, it depends on maximum thickness and the location of maximum thickness. engineering formulas for evaluating all scattering peaks were given in the paper. it is important for the design of low - rcs wing

    文摘:系統地揭示了翼形幾何參數對機翼的空間散射特性、極化散射特性的影響規律.研究發現，在垂直極化狀態下用理論尖劈公式計算機翼后緣繞射的計算結果與實驗結果相差甚遠.提出在垂直極化狀態下機翼后緣繞射的計算必須將后緣厚度考慮在內的見解.對於水平極化，前緣散射波峰只與前緣半徑有關；而對於垂直極化，前緣散射波峰與翼形最大厚度以及最大厚度位置有關.給出前後緣散射波峰的工程估算公式，為低雷達散射截面（ rcs ）機翼設計提供依據
  13. Fatigue life analysis of the leading - edge flap on x model aircraft

    某型飛機前緣機動襟翼使用壽命分析
  14. Abstract : approximate methods for calculating aerodynamic heating rates on space shuttles are discussed. various methods are given for predicting the heating rate at axisymmetric stagnation points, general three dimensional stagnationpoints and the leading edge stagnation point of wings. numerous laminar and turbulent heating techniques for flat plates and cones are analyzed and compared. a brief review of some methods is presented to predict heating rate for winward centerline and lateral direction off the symmetry plane. the results show that the methods are simpler and can guarantee enought precision for predicting aerodynamic heating environment of space shuttles

    文摘:介紹了國內外預測航天飛機氣動加熱的工程計算方法.給出了軸對稱、非軸對稱和機翼前緣等各種外形駐點熱流密度的計算，分析和比較了平板、錐體的層流和湍流熱流密度計算的各種方法，概述了航天飛機迎風面中心線和離開中心線橫向熱流密度的計算.計算結果表明，本文方法用在航天飛機氣動熱環境初步設計中比較簡單並且有足夠精度
  15. Because these projectiles attain hypervelocity within the atmosphere and are subjected to enormous heating as well as aerodynamic loads, the survivability of the front region of projectile wing is very important for designer to consider

    由於這類彈丸在大氣中高速飛行，並受到劇烈的氣動加熱及空氣動力負荷的作用，因此，彈翼前緣部的生存能力就成為彈丸設計中必須要考慮的問題。
  16. The model is solved with the finite difference method, the simulation software is organized to simulate the transient thermal response of the front region of projectile wing such as those launched by electrothermal chemical guns

    採用有限差分法進行數值求解，並編制了較為通用的模擬軟體，用於模擬諸如由電熱化學炮發射的高超聲速穿甲彈彈翼前緣的瞬時熱效應。
  17. The receiver aircraft is fitted with a probe that extends out from the side of the fuselage or from the leading edge of the wing

    受油機裝備有一個從機身一側或者是機翼前緣伸出的探頭。
  18. Experimental studies on leading - edge vortex breakdown and control of flow over 76 176 ; 40 176 ; double delta wing

    雙三角翼前緣渦破裂及其控制實驗研究
  19. Leading - edge root extensions lersx

    翼前緣延伸面
  20. Experimental investigation for the effects of vectored trailing - edge jets on the leading - edge vortex reakdown of a double delta wing

    雙三角翼前緣剖面形狀對渦運動的影響
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