AERODYNAMIC ANALYSIS OF SUBSONIC VERTICAL TAKE-OFF AND LANDING AIR VEHICLE

THE ADVENT OF THE CORDRAY ROTARY ENGINE HAS MADE POSSIBLE SUBSTANTIAL INCREASES IN THE POWER TO WEIGHT RATIO AVAILABLE TO THE AIRCRAFT DESIGNER. ENGINE SELECTION IS HISTORICALLY THE PRIMARY DETERMINATIVE OFVEHICLE DESIGN AND PERFORMANCE. THE AVAILABILITY OF THIS ENGINE ALONGWITH ADVANCES IN COMMAND AND CONTROL ELECTRONICS MAKES POSSIBLE A NEW CLASS OF VEHICLE CAPABLE OF VERTICAL TAKE OFF AND THEN TRANSITIONING TO HORIZONTAL FLIGHT A MID SUBSONIC SPEEDS AND THEN TRANSITIONING BACKTO HOVER FOR LANDING OR MISSION OBJECTIVES. THIS VEHICLE WOULD HAVE SUFFICIENT POWER FOR TAKE OFF WITH FULL FUEL AND REASONABLE PAYLOAD WEIGHTS WITH ADEQUATE PERFORMANCE RESERVES FOR LONG RANGE OPERATION AND HIGH ALTITUDE HOVER USING A DUCTED FAN PROPULSION SYSTEM. THE PHASE I OBJECTIVE IS TO PERFORM AERODYNAMIC ANALYSIS AND WIND TUNNEL TESTING OF A SCALE MODEL VEHICLE IN ORDER TO EVALUATE STABILITY AND CONTROL IN BOTH HOVER AND HORIZONTAL FLIGHT MODES AS WELL AS EVALUATION OF DRAG COMPONENTS AND TO ESTABLISH CRITERIA FOR A PHASE II UNMANNED AIR VEHICLE WITH A TAKE OFF WEIGHT OF 250 POUNDS.