The numerical simulations and analyses based on experimental results were carried out by means of computational fluid dynamics. Before now, many experimental and numerical approaches have been conducted for the model whose cross sectional configuration of the fuselage is an isosceles right triangle. It has high lift at high angle of attacks. With these results, new configurations were created to enhance the aerodynamic characteristics and it was obtained that a lift coefficient is increased. The reasons of its increment are analyzed and they are related to the strength of separation vortex and its position. Also, drag coefficients and pitching moment coefficients are discussed in this paper.