Forebody vortex flow control on the F-16C using tangential slot and jet nozzle blowing

The present experimental investigation of the effects of tangential slot and nozzle forebody blowing on the aerodynamic and stability characteristics of the F-16C configuration, for up-to-55 deg alpha and up-to-20 deg sideslip, was conducted on a 1/15th-scale model at freestream Mach = 0.4 and Re of 2.5 million/ft, for one tangential slot-nozzle location and two chordwise jet nozzle locations. Both the slot and the jet nozzles generated large yawing moments at very low blowing rates, over a wide range of alpha and sideslip angles. The centers of pressure of the side forces which generated the yawing moments due to slot and nozzle blowing were located in the region of the leading-edge extensions (LEXs); the moments may accordingly be due to the manipulation of the combined forebody and LEX flowfields.