Three-dimensioanl Navier-Stokes solutions were obtained for the external flow around three single-engine body-empennage configurations using the PAB3D code. These solutions were used to study afterbody drag reduction techniques. The configurations were solved at Mach 0.6 and 0 deg angle of attack and consisted of the following: (1) a baseline cased for which experimental data was available, (2) a contoured modification based on the area rule, and (3) elliptic cross section modifications designed to take advantage of the favorable pressure in the tail stagnation regions. The area rule modification resulted in a 6.3 % reduction in afterbody/nozzle drag and an 8.5 % decrease in total aft end drag. While the afterbody/nozzle drag for the elliptic cross section case showed a 15.4 % decrease from the baseline, the increased pressure dag of the tails resulted in a net decrease of only 1.1 % for the body-empennage configuration.


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    Title :

    Computational analysis of drag reduction techniques for afterbody/nozzle/empennage configurations


    Additional title:

    Computerunterstützte Untersuchung von Widerstandsverminderungstechniken für Rumpf/base/Leitwerk Konfigurationen


    Contributors:

    Published in:

    Publication date :

    1991


    Size :

    28 Seiten, 11 Bilder, 4 Tabellen, 20 Quellen



    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




    Computational Analysis of Drag Reduction Techniques for Afterbody/Nozzle/Empennage Configurations

    Abdol-Hamid, Khaled S. / Jones, William T. | SAE Technical Papers | 1991





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    Gogoi, A. / Rao, K. / American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 2003