Drag Reduction on the Fuselage Shape

Abstract

Under the constraint of pilot perspective angle, fuselage loading space, and the tail-down angle of after body, to change the parameters of the nose camber, the middle fuselage section’s flatness, roundness, and after-body contract ratio. Use CFD numerical simulation to assess the fuselage’s viscous drag, pressure drag, and longitudinal moment, attain the fuselage shape with low drag and acceptable longitudinal moment. The analysis and study show that the cross section profile of fuselage have greater impact on the fuselage pressure drag and longitudinal moment.