AN EXPERIMENTAL PROGRAM OF TWO-YEAR DURATION FOCUSED ON ACHIEVING SIGNIFICANT PRESSURE DRAG REDUCTION ON A HELICOPTER FUSELAGE IS DESCRIBED. THE WORK IS FOCUSED ON ACTIVE FLOW CONTROL (AFC) APPLIED TO A GENERIC NASA ROBIN HELICOPTER FUSELAGE USING SURFACE MOUNTED DIELECTRIC BARRIERDISCHARGE (DBD) PLASMA ACTUATORS. THE FLOW CONTROL EXPERIMENTS ARE TO BE PERFORMED AT A REYNOLDS NUMBER (BASED ON FUSELAGE LENGTH L) OF REL =2.65 X 1.06 AND MACH NUMBER M = 0.12. THESE PARAMETERS ARE COMPARABLE TO OTHER ONGOING ROBIN FUSELAGE AFC STUDIES INVOLVING EITHER SYNTHETIC JETS OR COMBUSTIONS ACTUATORS. IN THIS MANNER. THE RESULTS OF THIS STUDY WILL PROVIDE IMPORTANT ARCHIVAL DATA BY WHICH THE EFFICACY OF DBD PLASMA FLOW CONTROL FOR HELICOPTER DRAGREDUCTION MAY BE OBJECTIVELY ASSESSED. THE PLASMA ACTUATION WILL TAKE THE FORM OF BOTH STEADY AND PULSED PLASMA INDUCED TANGENTIAL BLOWING AS WELL AS THE APPLICATION OF PLASMA STREAM WISE VORTEX GENERATORS (PSVG). A FOCUS OF THE STUDY WILL BE TO DEVELOP AN OPTIMIZED PLASMA FLOW CONTROLSTRATEGY FOR DRAG REDUCTION. THIS WILL MOST LIKELY INVOLVE IMPLEMENTATION OF BOTH SPANWISE-ORIENTED PLASMA ACTUATORS AND PSVG USED IN COMBINATION WITH LOCAL PASSIVE SHAPE MODIFICATIONS DESIGNED TO MAXIMIZE THE AERODYNAMIC BENEFIT OF THE PLASMA FLOW CONTROL. MEASUREMENTS TO BE PERFORMED (WITH AND WITHOUT PLASMA FLOW CONTROL) INCLUDE FUSELAGE DRAG SURFACE PRESSURE SURFACE FLOW VISUALIZATION AND LDV AND PLY WAKE SURVEYS.