A NACA 0012 wing tip was tested at Mach 0.75 and chord Reynolds number of 3 million at incidences from 4 to 7 deg in a transonic Ludwieg tube. The Mach and Reynolds numbers are representative of full-scale rotorcraft blades. Because of the short test time of 0.1 s and high impulse loads, a dynamic calibration was applied to a conventional sidewall force balance to compensate for stress waves propagating within the force balance and test article. Numerical simulations of the entire test section were accomplished to provide data for comparison. The compensated, experimental lift and drag data compared well with the numerical results. This suggests that dynamic calibration improved the experimental data. This comparison demonstrates the feasibility of using complex models for calibrating short-duration wind tunnels in concert with numerical simulation.


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    Title :

    Force Measurements and Computational Validation of a Transonic Wing-Tip Flow


    Contributors:

    Published in:

    Journal of Aircraft ; 53 , 6 ; 1606-1613


    Publication date :

    2016-05-04


    Size :

    8 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English








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