A two dimensional wind tunnel test was conducted to obtain the quasisteady and unsteady characteristics of an advanced airfoil designed for helicopter rotor applications. Differential pressures were measured at 17 locations along the chord of the airfoil model. The airfoil motions were sinusoidal forced-pitch oscillations about the quarter chord at amplitudes varying from 2.5 to 10.0 degrees and at frequencies from 23 Hz to 90 Hz. The quasisteady tests were conducted at Mach numbers from 0.2 to 0.9, and the oscillatory tests between M = 0.2 and M = 0.7. At quasisteady conditions a limited number of drag measurements were made with a wake-traversing probe.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Two-Dimensional Wind Tunnel Test of an Oscillating Rotor Airfoil, Volume 1


    Contributors:

    Publication date :

    1977


    Size :

    168 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English