The feasibility of using static wind tunnel tests to obtain information about spin damping characteristics of an isolated general aviation aircraft tail was investigated. A representative tail section was oriented to the tunnel free streamline at angles simulating an equilibrium spin. A full range of normally encountered spin conditions was employed. Results of parametric studies performed to determine the effect of spin damping on several tail design parameters show satisfactory agreement with NASA rotary balance tests. Wing and body interference effects are present in the NASA studies at steep spin attitudes, but agreement improves with increasing pitch angle and spin rate, suggesting that rotational flow effects are minimal. Vertical position of the horizontal stabilizer is found to be a primary parameter affecting yaw damping, and horizontal tail chordwise position induces a substantial effect on pitching moment.


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    Titel :

    An Experimental Study of the Effect of Tail Configuration on the Spinning Characteristics of General Aviation Aircraft


    Beteiligte:
    M. G. Ballin (Autor:in)

    Erscheinungsdatum :

    1982


    Format / Umfang :

    182 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch






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