This report presents the results of tests made in the 7-by 10-foot wind tunnel and in the 20-foot tunnel of the National Advisory Committee for Aeronautics to determine the drag of a number of airplane wheels, wheel fairings, and landing gears designed or selected for an airplane of 3,000 pounds gross weight. All tests were made on full-size models; those in the 7-by 10-foot tunnel were made at air speeds up to 80 miles per hour and those in the 20-foot tunnel were made at air speeds up to 100 miles per hour. Although most of the landing-gear tests were made in conjunction with a fuselage and at 0 degree pitch angle, some of the tests were made in conjunction with fuselage plus wings and a radial air-cooled engine and at pitch angles from -5 degrees to 6 degrees to obtain an indication of the general effect of these various items on landing-gear drag. All tests were made in the absence of propeller slipstream.


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    Titel :

    The Drag of Airplane Wheels, Wheel Fairings, and Landing Gears - I


    Beteiligte:

    Erscheinungsdatum :

    1935-01-01


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch



    Drag of airplane wheels, wheel fairings, and landing gears

    Herrnstein, Jr., W.H. / Biermann, D. | Engineering Index Backfile | 1934


    Drag of Airplane Wheels, Wheel Fairings and Landing Gears-I

    W. H. Herrnstein / D. Biermann | NTIS | 1934


    The Drag of Airplane Wheels, Wheel Fairings, and Landing Gears - III

    Herrnstein, William H , Jr / Biermann, David | NTRS | 1936