Computational investigation of a pneumatic forebody flow control concept

Computational fluid dynamics is used in the analysis of the effectiveness of a tangential slot blowing concept for the generation of lateral control forces on an aircraft forebody. Multiple-zone, thin-layer Navier-stokes codes are used in the computation of the flow of a fighter forebody. An actuator plane is used to model the tangential slot blowing. The positioning of the slot near the nose of the aircraft increases the efficiency of the system. However, the length and circumferential location of the slot are not of prime importance.