Aerodynamic investigations were conducted in a transonic pressure tunnel on an 0.015 scale model of the space shuttle orbiter. Major test objectives were to determine: (1) transonic differential elevon/aileron lateral control optimization; (2) transonic elevon hinge moments; (3) transonic effects of the baseline 6 inch elevon/elevon and elevon/fuselage gaps; and (4) transonic effects of the short OMS pods. Six-component aerodynamic force and moment, and elevon hinge moment data, were recorded over an angle-of-attack range form -2 to +22 degrees. (Author)


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    Titel :

    Results of Differential Elevon/Aileron Deflection for Lateral Control Optimization and Elevon Hinge Moment Investigations on an 0.015-Scale Model (49-0) of the Space Shuttle Orbiter in the NASA/Langley Research Center 8 Foot Tpt (OA116)


    Beteiligte:
    A. I. Lindsey (Autor:in) / M. D. Milam (Autor:in)

    Erscheinungsdatum :

    1974


    Format / Umfang :

    278 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch