2-dimensional wind tunnel investigation conducted in Langley airfoil test apparatus; tests ranged in Reynolds number from 2.4 × 106 to 2.8 × 106 and in angle of attack from -- 10 to 12°; chordwise pressure distributions and schlieren flow photographs presented without analysis.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Chordwise pressure distributions over several NACA 16-series airfoils at transonic mach numbers up to 1.25


    Additional title:

    NASA -- Memo


    Contributors:


    Publication date :

    1959


    Size :

    285 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :



    Chordwise Actuation Effects on NACA 0012 Morphing Airfoils

    Rocha dos Santos, Artur G. / Caselato de Sousa, Guilherme L. / Sanches, Augusto C. et al. | AIAA | 2018


    Chordwise Actuation Effects on NACA 0012 Morphing Airfoils (AIAA 2018-3957)

    dos Santos, Artur G. Rocha / de Sousa, Guilherme L. Caselato / Sanches, Augusto C. et al. | British Library Conference Proceedings | 2018