THE PURPOSE OF THE PROPOSED RESEARCH IS TO TEST A METHOD FOR IMPROVING THE PERFORMANCE OF AIRCRAFT HIGH-LIFT SYSTEMS. DURING TAKEOFF AND LANDING COMMERCIAL AIRCRAFT UTILIZE HIGH-LIFT SYSTEMS SUCH AS SLATS AND FLAPS TO ENSURE THAT THE WINGS PROVIDE ENOUGH LIFT FOR SAFE OPERATION AT THE RELATIVELY LOW SPEEDS OF THESE PHASES OF FLIGHT. IMPROVED HIGH-LIFT PERFORMANCE AFFECTS THE TAKE-OFF FIELD LENGTH CLIMB RATE AND LANDING APPROACH SPEED. FOR A GIVEN AIRCRAFT DESIGN INCREASING THE LIFT IN THE HIGH-LIFT CONFIGURATION ALLOWS FOR SHORTER FIELD LENGTHS OR HIGHER PAYLOADS. INCREASING THE LIFT-TO-DRAG RATIO (BY INCREASING LIFT AND/OR DECREASING DRAG) CONTRIBUTES TO REDUCTIONS IN FUEL CONSUMPTION. ONE CONCEPT FOR INCREASING LIFT IN A HIGH-LIFT CONFIGURATION IS THE MICROJET: A SMALL NOMINALLY-ORTHOGONAL JET LOCATED CLOSE TO THE TRAILING EDGE OF AN AIRFOIL. LIFT ENHANCEMENT HAS BEEN PREDICTED AND EXPERIMENTALLY OBSERVED FOR SINGLE ELEMENT AIRFOILS BUT THE CONCEPT HAS NOT BEEN TESTED ON THE FLAP OF A MULTI-ELEMENT AIRFOIL. COMPUTATIONAL FLUID DYNAMICS (CFD) SIMULATIONS INDICATE THAT A MICROJET IN THIS LOCATION COULD INCREASE LIFT AND REDUCE DRAG WITH A RELATIVELY LOW OPERATING PRESSURE REQUIREMENT. WE PROPOSE TO DESIGN AND BUILD AN AIRFOIL MODEL FOR TESTING IN A WIND TUNNEL IN ORDER TO EXPERIMENTALLY VALIDATE THE CONCEPT OF A MICROJET ON THE FLAP OF A MULTI-ELEMENT AIRFOIL AND TO PROVIDE DATA FOR VALIDATION OF CFD MODELING. THE MODEL WILL HAVE A CONSTANT CROSS-SECTIONAL PROFILE BASED ON THE NLR 7301 AIRFOIL WHICH CONSISTS OF A MAIN ELEMENT AND A FLAP. WE HAVE STUDIED THIS AIRFOIL EXTENSIVELY USING CFD TO SIMULATE THE EFFECTS OF MICROJETS. THE MODEL WILL INCORPORATE INTERNAL CHANNELS TO DELIVER AIR TO MICROJET SLOTS LOCATED NEAR THE TRAILING EDGE OF THE FLAP. SURFACE PRESSURE AND TEMPERATURE WILL BE MEASURED INSIDE THE MICROJET PLENUM. SURFACE PRESSURE PORTS WILL ALSO BE INCLUDED ALONG THE CHORDWISE EXTENT OF THE MAIN AIRFOIL AND FLAP TO ENABLE MEASUREMENT OF THE LIFT FORCE AND PITCHING MOMENT VIA SURFACE PRESSURE INTEGRATION. THE DRAG FORCE WILL BE MEASURED DOWNSTREAM OF THE MODEL USING A WAKE RAKE. ACCURATE CHARACTERIZATION OF MICROJET PERFORMANCE BASED ON EXPERIMENTAL RESULTS IS AN IMPORTANT STEP IN EVALUATING THE POTENTIAL FOR APPLICATION OF THIS DEVICE TO FUTURE AIRCRAFT. IF POTENTIAL GAINS IN HIGH-LIFT PERFORMANCE ARE REALIZED THEY WILL ADVANCE PROGRESS TOWARDS MORE EFFICIENT AND FLEXIBLE FUTURE AIR VEHICLES AS ENVISIONED IN NASA ARMD S STRATEGIC THRUST 3: ULTRA-EFFICIENT COMMERCIAL VEHICLES.