An investigation has been made in the Langley 4 by 4-foot supersonic pressure tunnel at Mach numbers of 1.82 and 2.01 to determine the longitudinal and lateral static-stability characteristics of a 0.04-scale model of the Lockheed F-104A airplane. The effects of a modified vertical tail, several ventral-fin arrangements, and several external store arrangements were also determined. The tests were made at Reynolds numbers of 1.02 (exp 6) and 1.382 (exp 6), respectively, based on the wing mean geometric chord. The tests were made of combined angles of attack and sideslip that varied from about -4 deg. to about 20 deg.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Longitudinal and Lateral Stability Characteristics of a 0.04-Scale Model of the Lockheed F-104A Airplane at Mach Numbers of 1.82 and 2.01. Coord. No. AF-245


    Contributors:

    Publication date :

    1956-08-06


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English