A new formulation of helicopter rotor thickness, noise for hover and forward flight, is discussed. The parameters required for this formulation are rotor motion, planform and airfoil thickness distribution. A computer program has been developed to calculate the pressure signature due to blade thickness for a helicopter in arbitary motion. Comparison with high-speed helicopter tests shows good agreement with calculations when the observer is in or near the horizontal plane in which the rotor disc lies. Characteristics of thickness noise are illustrated by numerical examples indicating strongly that the high-speed blade slap may be due primarily to the thickness effect. The methods of Deming and Arnoldi are discussed as the special cases of this technique.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Thickness Noise of Helicopter Rotors a High Tip Speeds


    Contributors:
    F. Farassat (author) / R. J. Pegg (author) / D. A. Hilton (author)

    Publication date :

    2004


    Size :

    12 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Thickness noise of helicopter rotors at high tip speeds

    FARASSAT, F. / PEGG, R. / HILTON, D. | AIAA | 1975


    Thickness Noise of Helicopter Rotors at High Tip Speeds

    Farassat, F. / Pegg, R. J. / Hilton, D. A. | NTRS | 1975


    Thickness noise of helicopter rotors at high tip speeds

    Farassat, F. / Pegg, R. J. / Hilton, D. A. | NTRS | 1975


    High-speed noise of helicopter rotors

    Shenoy, K. R. | NTRS | 1982


    Supersonic quadrupole noise theory for high-speed helicopter rotors

    Farassat, F. / Brentner, K.S. | Tema Archive | 1998