A performance study was made of the application of a jet-flap to a reaction-drive rotor for a heavy-lift helicopter mission and for a high-speed-helicopter maneuverability (200 knots, 2g) mission. The results of the study are as follows: As a result of the increase in maximum airfoil lift coefficient achieved by the jet-flap, rotor solidity is reduced with the jet-flap to approximately 59% of a nonjet-flap rotor. As a result of the saving in rotor solidity, and hence in rotor weight, the jet-flap configuration had a 21% higher productivity than a nonjet-flap configuration. Of the three propulsion systems studied utilizing a jet-flap (hot cycle, warm cycle, cold cycle) the hot cycle gave the largest increase in productivity. The 200 knot 2g mission is performed best with a warm cycle propulsion system. The jet-flap permits designing for a rotor blade loading coefficient C sub T/sigma = .170 at 2g without encountering blade stall. The jet-flap rotor permits a 200 knot 2g maneuver without suffering the penalty of an unreasonable rotor solidity that would be required by a nonjet-flap rotor.


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    Titel :

    A performance application study of a jet-flap helicopter rotor


    Beteiligte:
    Sullivan, R. J. (Autor:in) / Laforge, S. (Autor:in) / Holchin, B. W. (Autor:in)

    Erscheinungsdatum :

    1972-05-01


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    A Performance Application Study of a Jet-Flap Helicopter Rotor

    R. J. Sullivan / S. Laforge / B. W. Holchin | NTIS | 1972


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    Wei, F.-S. / Gates, A. / American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 2011


    Study of jet propelled helicopter rotor with jet flap

    Fiorini, V. | Engineering Index Backfile | 1961