Results are presented on models having range of airfoil thickness from 3 to 12% chord for single and double wedge airfoils and tapered planforms and from 9 to 20% chord for double wedge airfoils and square planforms; for test parameters, in general, thickness effects are destabilizing at higher Mach but stabilizing at subsonic and transonic Mach numbers.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Aerodynamic effects of some configuration variables on aero-elastic characteristics of lifting surfaces at Mach numbers from 0.7 to 6.86


    Additional title:

    NASA -- Tech Note


    Contributors:


    Publication date :

    1961


    Size :

    51 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :