抄録
Wing characteristics have been analyzed for long term, however it has been scarcely described about difference of pressure distribution around the trailing edge between theories and experiments.One of the determining methods of wing characteristics is well known Kutta's condition. Kutta's condition is a method to avoid velocity infinity at the trailing edge.This paper cleared that stagnation point and singular point are simultaneously disappeared with Kutta's condition at the trailing edge using Joukowski translation.The pressure coefficient at the trailing edge has been analytically deduced as function of attack of angle, camber and wing thickness.
