Aerodynamic Optimal Engine Integration at the Fuselage Tail of a Generic Business Jet Configuration

Aerodynamic interference effects of jet engines installed at the tail of a generic business configuration are investigated using numerical flow simulations based on the solution of Euler equations. It is demonstrated that the channel con-tour formed by fuselage tail, pylon and nacelle dominates the flow behavior and also the resulting interference drag. A simulation based optimization process chain is then used to minimize the interference drag in cruise flight by applying the free-form deformation method for re-shaping of the fuselage tail