Accession Number : AD0473864


Title :   SUMMARY TECHNICAL REPORT, ROTOR/WING CONCEPT STUDY. VOLUME 2. APPENDIXES A, B, C, D, E AND F


Corporate Author : HUGHES TOOL CO CULVER CITY CA AIRCRAFT DIV


Personal Author(s) : Head, Robert E


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/473864.pdf


Report Date : Sep 1965


Pagination or Media Count : 183


Abstract : Research work including wind tunnel and whirl test of the Rotor/Wing is described. The Rotor/Wing is a dual-purpose lifting device that is a rotor with an unusually large hub. It acts as a tip-jet powered helicopter for low- speed flight and stops in flight to become a tapered and sweptback low-aspect ratio wing for cruise. Stopping the rotor in flight removes the speed limitations of the helicopter rotor and permits flight speeds up to 500 knots. Research work was supported by the U. S. Navy Office of Naval Research and Bureau of Naval Weapons. Three series of wind tunnel tests demonstrated that the powered-rotor and autorotating-rotor characteristics are similar to those of a high-performance helicopter; that the stopped-rotor characteristics are similar to a conventional low-aspect ratio wing with sweep and taper, and maximum lift/ drag ratios of 12 or more should be achievable for full-scale aircraft; and that conversion from stopped- to running- rotor and vice versa is a simple and straightforward procedure.


Descriptors :   *AIRCRAFT MODELS , *VERTICAL TAKEOFF AIRCRAFT , AERODYNAMIC LOADING , ANGLE OF ATTACK , AUTOGYROS , DRAG , FLUTTER , FORCE(MECHANICS) , HELICOPTER ROTORS , LIFT , MOMENT OF INERTIA , MOMENTS , PITCH(MOTION) , ROLL , ROTOR BLADES(ROTARY WINGS) , VIBRATION , WIND TUNNEL MODELS


Subject Categories : Aircraft
      V/STOL


Distribution Statement : APPROVED FOR PUBLIC RELEASE