Mean camber lines identical for six airfoils and of such form that max mean camber is 2% of chord and is at position 0.4 of chord behind leading edge; airfoils differ in thickness only, max thickness per chord ratios being 0.06, 0.09, 0.12, 0.15, 0.18 and 0.21.


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    Title :

    Tests of N.A.C.A. airfoils in variable-density wind tunnel, series 24


    Additional title:

    Nat Advisory Committee Aeronautics -- Tech Notes


    Contributors:
    Jacobs, E.N. (author) / Ward, K.E. (author)


    Publication date :

    1932


    Size :

    19 pages


    Remarks:

    14 Supp plates


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :


    Tests of N.A.C.A. Airfoils in variable-density wind tunnel

    Jacobs, E.N. / Pinkerton, R.M. | Engineering Index Backfile | 1936



    Tests of N.A.C.A. airfoils in the variable-density wind tunnel Series 230.

    Jacobs, Eastman N / Pinkerton, Robert M | NTRS | 1936


    Tests of N.A.C.A. Airfoils in variable-density wind tunnel, series 4e and 63

    Jacobs, E.N. / Pinkerton, R.M. | Engineering Index Backfile | 1931


    Tests of N.A.C.A. airfoils in the variable-density wind tunnel ; 5: Series 24

    Jacobs, Eastman N. / Ward, Kenneth E. | TIBKAT | 1931