An inviscid, nonconservative, three-dimensional full-potential flow code, ROT22, has been developed for computing the quasi-steady flow about a lifting rotor blade. The code is valid throughout the subsonic and transonic regime. Calculations from the code are compared with detailed laser velocimeter measurements made in the tip region of a nonlifting rotor at a tip Mach number of 0.95 and zero advance ratio. In addition, comparisons are made with chordwise surface pressure measurements obtained in a wind tunnel for a nonlifting rotor blade at transonic tip speeds at advance ratios from 0.40 to 0.50. The overall agreement between theoretical calculations and experiment is very good. A typical run on a CRAY X-MP computer requires about 30 CPU seconds for one rotor position at transonic tip speed.


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    Title :

    Computation of transonic flow about helicopter rotor blades


    Contributors:

    Published in:

    Publication date :

    1986-05-01



    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English


    Keywords :


    Computation of transonic flow about helicopter rotor blades

    ARIELI, R. / TAUBER, M. E. / SAUNDERS, D. A. et al. | AIAA | 1986



    Subsonic and Transonic Potential Flow over Helicopter Rotor Blades

    FRANCIS X. CARADONNA AND MORRIS P. ISOM | AIAA | 1972