Please use this identifier to cite or link to this item: `http://hdl.handle.net/11455/2699`
 標題: 二維翼剖面尾緣外形流場數值探討Numerical Analysis for Flow Over Airfoils with Different Shape of Trailing-Edge 作者: 徐昌晟Shyu, Chang-Sheng 關鍵字: Slab Trailing-Edge;平板尾緣;Divergent Trailing-Edge;發散型尾緣 出版社: 機械工程研究所 摘要: 本文主要研究目的，乃在探討不同尾緣 (Trailing-Edge)幾何外形流場之 特性。首先以橢圓形偏微分方程式及代數法建立適合本文物理模式之雙格 點分佈，再利用區域隱式(Locally Implicit) 數值法求解可壓縮納維爾- 史托克(Navier-Stokes)方程式。在進行各項不同尾緣外形之流場特性探 討之前，首先以 NACA 0012 及 RAE 2822 兩種不同之翼剖面進行程式驗 證，並與 AGARD AR-138 之實驗數據來作比較以確定程式之準確性。繼而 以 RAE 2822 翼剖面來分析，改變不同攻角時分離流區域大小對震波效應 之影響。本文所探討之不同尾緣外形，主要區分為兩個部分，第一部分 為 Slab Trailing Edge，外形以 NACA 64A 004M 對稱翼剖面加裝 Slab 於尾緣處。第二部分為 Divergent Traniling Edge外形，以尖尾緣之 RAE 2822 翼剖面為基本外形，利用不同尾緣厚度以及改變尾緣曲度為設 計參數，設計出四種不同之發散式尾緣外形。針對 Slab Trailing 及 Divergent Trailing-Edg翼剖面之數值探討結果發現，具有增加拱弧效 應(Camber effective- ness) 之 DTE 翼剖面於穿音速流場時較 RAE2822 翼剖面有較佳之升力及阻力係數。此外，由結果顯示 DTE具有分 隔尾緣區上、下表面壓力分佈之效應。The flow field of airfoil with different Trailing- Edge geometry have studied. For this research, the two -zone grid, created by solving elliptic partial diffe- rential equations and algebraic equs, was used. An locally implicit scheme is used for the numerical so- lution of the compressible Navier- Stokes equs. First, the NACA 0012 and RAE2822 airfoil were sel- ected to demonstrate the scheme program and compared with the experimental data of AGARD. Then, the RAE2822 airfoil was used to study a two-dimensional shock bou- ndary-layer interaction problem. In this study, the Trailing-Edge geometry was cla- ssified to two types. The first type is slab Trailing- Edge. For this Type, the slabs were add to Trailing- Edge of NACA 64A 004M airfoil. The second type is Divergent Trailing- Edge (DTE). For this type, the Trailing-Edge of RAE2822 airfoil was modified by variying surface curvature with constant Trailing-Edge thickness. Four different Divergent Trailing-Edge has been designed. In this study, flow over the airfoil with slab Trailing-Edge and Divergent Trailing- Edge are investi- gated. The results show that the increased camber eff- ectiveness of the Divergent Trailing-Edge airfoil has superior transonic lift and drag characteristics to RAE2822 airfoil. In addition, It is also found that the Divergent Trailing-Edge has effects to decouple the upper- and lower-surface pressure distributions near the Trailing- Edge. URI: http://hdl.handle.net/11455/2699 Appears in Collections: 機械工程學系所

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