Airborne Laser Turret Flow Control: A Parametric Study of Wind Tunnel Model Conditions

Wind tunnel tests were conducted on a one-third scale model of the USAF NKC-135 airborne laser turret and aerodynamic fairing. The model was constructed so that six main parameters could be varied as follows fairing nosepieces, fuselage bleed slot position and condition porousnon-porous, suction duct throttle position, blower suction throttle position, and the turret-fairing gap. The method of flow control employed to produce quiescent air flow about the turret was that of fuselage boundary layer and after-body fairing suction. Results of the extensive testing indicate that the method is viable for low velocity, incompressible air flow. Additionally, optimum conditions i.e. minimum suction required and the best combination of other parameters necessary to provide quiescent flow were determined.