Methods of thin airfoil theory have been extended to oblique or sweptback airfoils of finite aspect ratio moving at supersonic speeds. The cases considered thus far are symmetrical airfoils at zero lift having planforms bounded by straight lines. Because of the conical form of the elementary flow fields, the results are comparable in simplicity to the results of the two dimensional thin airfoil theory for subsonic speeds. In the case of untapered airfoils swept back behind the Mach cone the pressure distribution at the center section is similar to that given by the Ackeret theory for a straight airfoil. With increasing distance from the center section the distribution approaches the form given by the subsonic flow theory. The pressure drag is concentrated chiefly at the center section and or long wings a slight negative drag may appear on outboard sections.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Thin oblique airfoils at supersonic speed


    Contributors:


    Publication date :

    1976-02-01


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English


    Keywords :


    Thin oblique airfoils at supersonic speed

    Jones, R.T. | Engineering Index Backfile | 1946


    Thin oblique airfoils at supersonic speed

    Jones, Robert T. | TIBKAT | 1946


    Thin oblique airfoils at supersonic speed

    Jone, Robert T | NTRS | 1946


    Thin Oblique Airfoils at Supersonic Speed

    Jones, Robert T | NTRS | 1946


    Subsonic flow over thin oblique airfoils at zero lift

    Jones, R.T. | Engineering Index Backfile | 1947