Transonic pressure tunnel tests at Mach numbers from 0.25 to 1.00 were performed to determine the effects of area-rule additions to the sides of the fuselage on the aerodynamic characteristics of a 0.087 scale model of an NASA supercritical-wing research airplane. Presented are the longitudinal aerodynamic force and moment characteristics for horizontal-tail deflection angles of -2.5 deg and -5 deg with the side fuselage area-rule additions on and off the model. The effects of the side fuselage area-rule additions on selected wing and fuselage pressure distributions at near-cruise conditions are also presented.


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    Title :

    Aerodynamic Characteristics of an NASA Supercritical-Wing Research Airplane Model with and Without Fuselage Area-Rule Additions at Mach 0.25 to 1.00


    Contributors:

    Publication date :

    1972


    Size :

    133 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English