Wake vortex separation standards are used to prevent hazardous wake vortex encounters which mainly found in the final approach course within the airport termination zone. firstly, this paper analysis the mechanism of the vortex decay and research the influence on the safety of the flight ; then. several different radar wake vortex separation standards are compared and some basic guidelines are developed to establish the future vortex standards. in addition, one kind of advance vortex classification for the civil airplane is proposed. secondly, an encounter hazard model which established for the following aircraft and a simple vortex decay model which mostly concern with the proceeding one are developed ; and a safe separation model can be derived from the both. finally, through the simulation calculation, the correctness of the vortex classification of different types of aircrafts are tested and proved
本課題對雷達管制條件下的最小
尾流間隔標準進行了較為詳細的分析和研究；首先對
尾流的形成和消散機理以及
尾流對飛行安全的影響做出了詳細的分析，然後就目前實行的幾種不同的最小
尾流間隔標準進行了比較和分析，提出了相關的幾條準則和一種改進的機型
尾流分類標準；在這之後，採用理論分析和統計數據分析相結合的方法，建立了
尾流危險遭遇基本模型和
尾渦消散模型；並在此基礎上對民用航空不同機型的
尾流分類的合理性進行了計算和評估，為最小
尾流間隔標準的確定和改進提供了初步的理論依據。
Their maneuvering and control systems are made up of several propellers. this system has many disadvantages such as big volume, high consuming of energy, low total efficiency, high noise and vortex
它們使用的操縱和控制系統大多是由多個螺旋槳推進器組成的，這樣的系統體積大、重量大、能耗高、綜合效率低，並有較大的噪音和
尾渦。
The complex vortex system structure and shock wave system structure inside this rotor is obtained. wall flow patterns on the blade surface and hub surface are found out. the complex vortex system structure, such as horseshoe vortex, passage vortex, corner vortex and trailing vortex, and the interaction with shock wave system are researched. especially, the character of the tip clearance flow inside the rotor passage is revealed, and the interaction between shock wave and tip clearance flow near blade tip and the evolution of tip clearance flow are considered
給出了葉片表面及輪轂面上的壁面流型，分析並揭示了轉子葉道內的馬蹄
渦、通道
渦、角
渦、
尾渦等復雜
渦系及其與激波的相互干涉；特別是，分析並揭示了轉子葉道內頂隙射流的特點，得到了頂隙附近激波與泄漏流動的干涉形態及泄漏流動的發展，並著重給出了其與激波的干涉形態。
The surface panel method has been applied to predict the hydrodynamic performance of highly skewed propeller. the surface of propeller and its trailing vortex are discreted by a number of small hyperboloidal quadrilateral panels with constant source and doublet distribution. for highly skewed propeller, the conventional method generating grid oriented along constant radii will result in a high aspect ratio and a high skewness and a twist panel near the propeller tip on blade surface, which result easily in incorrect calculation results of velovity on blade surface, even in iteration divergence and calculation failure. a “ non - conventional grid ” is developed to acoid these problems. this grid can effectively solve the problem of the calculation and convergence for highly skewed propeller. the non - linear kutta condition of equal pressure on upper and lower at the trailing edge is executed by the iterative procedure. by sample calculating, the obtained results are satisfied the experimental data
採用面元法預報大側斜螺旋槳水動力性能，螺旋槳表面及
尾渦面離散為四邊形雙曲面元，每個面元上布置等強度源匯和偶極子分佈.對于大側斜螺旋槳而言，槳葉表面採用常規的等半徑網格劃分方法在近葉梢處將導致大展弦比、大側斜和扭曲面元，這容易使槳葉表面速度的計算結果不正確，甚至會導致迭代過程發散及計算失敗.文中建立了一種「非常規網格」劃分方法，能有效地解決大側斜螺旋槳的計算和收斂問題.槳葉隨邊處通過迭代實現非線性等壓庫塔條件
In lifting - surface theory, the non - liner phenomena of the trailing vortex in the transition wake area and of the tip vortex separation are considered. in surface panel method hyperboloidal quadrilateral panels are employed and the morino ' s analytical formulation is used to determine the influence coefficients. the more reasonable pressure kutta condition is satisfied at the trailing edge of propeller blade
在計算中，對于升力面理論，本論文考慮了過渡區
尾渦收縮和葉梢分離的非線型現象的影響；對于面元法，本論文採用的是計算較為簡便的基於擾動速度勢的基本公式及雙曲面形狀的面元，在槳葉隨邊滿足更趨合理的壓力kutta條件，並用morino導出的解析公式計算面元的影響系數的快速有效的數值預報方法。
Large eddy simulation of particle wake effect and rans simulation of turbulence modulation in gas - particle flows
顆粒
尾渦增強湍流的大
渦模擬以及氣固兩相流中湍流變動的數值模擬
The results are compared with the cases in a single - layer fluid, showing that the density stratification can have a relative large effect on the drag and lift coefficients as well as the vortex shedding
計算受迫振蕩圓柱體的升力系數、阻力系數隨時間的演化曲線和圓柱體的
尾渦分佈，以及圓柱體的受迫振蕩激發兩層流體內界面的擾動，並與均勻流體的情況進行了比較分析。
The aerodynamic interference between the shroud and the propeller is calculated by lifting line theory. its precise, proved by wind tunnel test here, satisfies the engineering demand
在計算螺旋槳的參數時，仍以有限葉數升力線模型進行處理，並用誘導因子法來計算槳葉
尾渦系在升力線上產生的誘導速度。
The duct and it ' s vortex is discreted by a number of small straight quadrilateral panel. constant source and doublet distribution is placed on each panel on the surface of body, and constant doublet distribution is placed on each panel on the surface of vortex
以面元的幾何形心為控制點，在每個物面面元的控制點上布置等強度的源匯分佈和偶極子分佈，每個
尾渦面面元控制點上布置等強度的偶極子分佈。
Engineers are working on ways to detect hazardous wake vortices so pilots can avoid them or to design aircraft that leave safer skies behind them
工程師正在研究，想找出有效的點子，偵測危險的機
尾渦流，或設計不會危及後方空域的安全飛機。
Trailing vortex cavitation
尾渦空化
