Comparison of algebraic turbulence models for afterbody flows with jet exhaust

Three-dimensional Navier-Stokes simulations have been done for transonic and low supersonic flow past a nonaxisymmetric nozzle typical of those advocated for advanced fighter airplanes. The jet exhaust is included in the calculations. The investigation compares the performance of the unmodified Bald...

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Bibliographic Details
Published in:AIAA journal 1992-11, Vol.30 (11), p.2716-2722
Main Authors: Compton, William B, Abdol-Hamid, Khaled S, Abeyounis, William K
Format: Article
Language:English
Subjects:
Aerodynamics
Compressible flows
shock and detonation phenomena
Exact sciences and technology
Fluid dynamics
Fundamental areas of phenomenology (including applications)
Physics
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Summary:Three-dimensional Navier-Stokes simulations have been done for transonic and low supersonic flow past a nonaxisymmetric nozzle typical of those advocated for advanced fighter airplanes. The jet exhaust is included in the calculations. The investigation compares the performance of the unmodified Baldwin-Lomax turbulence model with its performance when enhanced by the Degani-Schiff and the Goldberg modifications. Solutions are presented for Mach numbers of 0.80, 0.94, and 1.20 at 0-deg angle of attack and a Reynolds number of 20 x 10 to the 6th. The numerical results, which are compared to the wind-tunnel data, show that the three turbulence models predict considerably different shock locations, separated-flow regions, and flowfields.
ISSN:0001-1452
1533-385X
DOI:10.2514/3.11289