As part of a propulsion/airframe integration program at Langley Research Center, tests were conducted in the Langley 16-Foot Transonic Tunnel to determine the effects of locating flow-through mixed flow engine nacelles in several aft underwing positions on the longitudinal aerodynamics of a high wing transport airplane. D-shaped inlet nacelles were used in the test. Some configurations with antishock bodies and with nacelle toe-in were also tested. Data were obtained for a free stream Mach number range of 0.70 to 0.85 and a model angle-of-attack range from -2.5 to 4.0 degrees.


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    Title :

    Effect of Location of Aft-Mounted Nacelles on the Longitudinal Aerodynamic Characteristics of a High-Wing Transport Airplane


    Contributors:

    Publication date :

    1990


    Size :

    98 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English