三維機翼尾端跡流之研究

Abstract

本文以三維翼面尾端跡流為主要研究之對象，尋找均勻流流經此翼面之尾跡流位置。本文假設流場內之流體滿足勢流，利用邊界積分方程式使用高斯積分法對離散後的邊界積分方程式進行積分，求解此翼面表面上之速度勢。將翼面邊界上所求的尾端環流量帶入邊界積分式以求解流場中各點位置的速度勢，再藉由改變尾跡流的形狀來觀察法向速度。本文嘗試利用最小方差的方式將勢流理論解在跡流面上的法向速度最小化為目標，希望能有效的尋找出三維尾翼跡流的位置，而不再需要其他額外的輔助工具。

This study focuses on how to locate the wake position of a three-dimensional airfoil due to a uniform flow. Based on the potential theory, the boundary integral method is applied to solve the velocity potential on the boundary of the airfoil. Once the strength of the velocity potential is solved, it can be substituted into the boundary integral equation and find all the velocity potential in the flow field. By adjusting the shape of the wake, and minimizing the normal velocity components on the surface of the wake, the goal is to select a correct position of wake.