Fuselage Shape Optimization of a Wing–Body Configuration with Nacelles

An aerodynamic design tool that combines a computational fluid dynamics code with an optimization technique for a drag minimization is developed and applied to a fuselage shape optimization of a Mach 1.7 scaled supersonic experimental airplane. An airframe/nacelle integration is taken into consideration. The optimized fuselage is compared with a conventional axisymmetrical area-ruled fuselage designed by a linear theory. The results indicate that a nonaxisymmetrical fuselage design concept with this optimization design tool is effective for the reduction of pressure drag, especially in the design of an airplane that generates a strong interference drag between its airframe and nacelles.