The results of a flight research program conducted to determine the behavior of a fully articulated, servo-flap controlled rotor system at various power levels in highspeed flight are presented. The research aircraft, instrumentation, and test program are described. A standard Kaman UH-2 helicopter was modified by the addition of a General Electric YJ-85 jet engine, without afterburner, mounted on the right side of the fuselage for horizontal thrust augmentation. Research flights were conducted up to a level-flight true airspeed of 188 knots. Airspeeds limited by retreating blade stall or advancing blade compressibility were established. The effects of density altitude, rotor speed and power, tip speed ratio, thrust augmentation and aircraft gross weight on the limit airspeeds are discussed. It is concluded that the speed envelope for rotary wing aircraft can be substantially expanded by unloading the main rotor through the application of horizontal thrust augmentation. (Author)


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    UH-2 Helicopter High-Speed Flight Research Program Utilizing Jet Thrust Augmentation


    Contributors:

    Publication date :

    1965


    Size :

    2 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English





    Use of thrust and lift augmentation for increasing helicopter operating speed

    Robinson, Jr., D.W. | Engineering Index Backfile | 1963


    Double-thrust high-speed combined type unmanned helicopter

    XU ANAN / WANG FANG / CHEN MING | European Patent Office | 2024

    Free access

    Flight program on NH-3A research helicopter

    Fradenburgh, E.A. / Chuga, G.M. | Engineering Index Backfile | 1968


    Rotor flow research in low speed helicopter flight

    Velkoff, H.R. | Tema Archive | 1981