At the request of the Bureau of Ordnance, Department of the Navy, the Langley Pilotless Aircraft Research Division has initiated a program to investigate the general aerodynamic characteristics of the Naval Ordnance Test Station's SIDEWINDER missile. The model used in the flight test presented herein was a full-scale, rocket-propelled test vehicle. This paper presents the results from a flight test investigation using the pulsed-control technique to determine the static and dynamic longitudinal stability and control derivatives and drag data for a canard-missile configuration. The methods for obtaining these data are presented in references 1 and 2. This investigation was conducted at a small angle-of-attack range and for a Mach number range of 1.2 to 2.1. The model used in this investigation was flight-tested at the Langley Pilotless Aircraft Research Station at Wallops Island, Va.


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    Title :

    Flight Investigation at Low Angles of Attack to Determine the Longitudinal Stability and Control Characteristics of the Sidewinder Missile at Mach Numbers from 1.2 to 2.1


    Contributors:

    Publication date :

    1955-11-02


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English