Wind tunnel tests were conducted to determine the stability and control characteristics of a monoplane missile with large delta wings and various tail configurations. The tests were conducted at angles of attack of approximately 24 degrees and angles of sideslip of about 22 degrees. Tail control configurations were the cruciform, conventional airplane type, and an inverted airplane configuration. Control effectiveness was measured for pitch, yaw, and roll. (Author)


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Stability and Control Characteristics of a Monoplane Missile with Large delta Wings and Various Tail Controls at Mach 1.90 to 2.86


    Contributors:

    Publication date :

    1974


    Size :

    41 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English