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Theoretical analysis of aircraft afterbody flow (1987)

Nakahashi, Kazuhiro ; Andrews, Alison E. ; Deiwert, George S.

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Publication Date: 2011-08-19

Description: Computational methods solving the thin shear layer formulation of the compressible, Reynolds-averaged Navier-Stokes equations are presently used to investigate the strongly interactive flow field about aircraft afterbodies. Solutions for a variety of axisymmetric afterbody and nozzle geometries are solved by means of a time-dependent implicit numerical algorithm for both subsonic and supersonic external flows, and the results obtained are compared with experimental data. A novel adaptive-grid technique is used to resolve flow regimes having large gradients, as well as to improve the accuracy and efficiency of the computational scheme.

Keywords: AERODYNAMICS

Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 24; 496-503

Format: text

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