:2nd Report, Cases When the Trailing Edge Has a Finite Summit Angle

概要

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The authors had analytically deduced the pressure coefficient at the trailing edge of Joukowski wing with Kutta's condition as functions of angle of attack, camber and wing thickness. It had been cleared that stagnation point and singular point are simultaneously disappeared with Kutta's condition at the trailing edge using Joukowski translation. This paper describes the pressure coefficient near the trailing edge of several Karman-Trefftz wings with Kutta's condition as functions of summit angle of trailing edge. As a result, when the trailing edge angle has less than ten degrees, it is physically meaningless that theoretical pressure coefficient increases suddenly near the trailing edge. Furthermore, the authors propose a method using a very thin plate to improve airfoil performance at the trailing edge.
一般社団法人日本風力エネルギー学会の論文