An experimental investigation has been conducted in the Langley stability tunnel at low speed to determine the pitching stability derivatives of a 1/9-scale powered model of the Convair XFY-1 vertically rising airplane. Effects of thrust coefficient, control deflections, and propeller blade angle were investigated. The tests were made through an angle-of-attack range from about -4deg to 29deg, and the thrust coefficient range was from 0 to 0.7. In order to expedite distribution of these data, no analysis of the data has been prepared for this paper.


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    Titel :

    Wind-Tunnel Investigation at Low Speed of the Pitching Stability Derivatives of a 1/9-Scale Powered Model of the Convair XFY-1 Vertically Rising Airplane, TED No. NACA DE 373


    Beteiligte:
    Queijo, M. J. (Autor:in) / Wolhart, Walter D. (Autor:in) / Fletcher, H. S. (Autor:in)

    Erscheinungsdatum :

    1953-07-13


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch