Program to obtain data on thick airfoils to be used for pressure-jet rotor system; hovering performance of rotor for tip Mach number from 0.27 to 0.76 and corresponding blade tip Reynolds number range; performance characteristics of thick airfoils may be seriously limited by stall starting at trailing edges of airfoils; hovering performance of rotor with vortex generator compared with smooth-blade rotor.


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    Title :

    High-tip-speed static-thrust tests of rotor having NACA 63215 A018 airfoil sections with and without vortex generators installed


    Additional title:

    NASA -- Tech Note


    Contributors:


    Publication date :

    1960


    Size :

    21 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :