A computational study of subsonic flowfields over a missile configuration

Date

1997-01-06

Author

Uygun, Murat
Tuncer, İsmail Hakkı

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URI

https://hdl.handle.net/11511/77204

Conference Name

AIAA Aerospace Sciences Meeting and Exhibit, (6 - 09 Ocak 1997)

Collections

Department of Aerospace Engineering, Conference / Seminar

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A computational study of subsonic flows over a medium range cargo aircraft Uygun, Murat; Tuncer, İsmail Hakkı (2003-01-01) Inviscid and viscous flows over CN-235 cargo aircraft are computed at cruise conditions and at angles of attack ranging from 0 deg to 5 deg using CFD-FASTRAN Navier-Stokes solver. Computations are performed on a Pentium III based PC with a 1Gb memory. Grid sensitivity and verification studies are performed on clean-wing and wing-nacelle configurations to determine the effects of the surface grid density, the size of the computational domain and available numerical schemes. Inviscid and viscous flows with av...
A computational study of flow separation characteristics and wake profiles behind a flapping airfoil Tuncer, İsmail Hakkı (1999-01-01) © 1999 American Institute of Aeronautics and Astronautics, Inc. All rights reserved.Unsteady, viscous flowfields over a NACA0012 airfoil oscillated in plunge and/or pitch at various reduced frequency, amplitude and phase shift are computed. Vortical wake formations, boundary layer flows at the leading edge, the formation of leading edge vortices and their downstream convection are presented in terms of unsteady particle traces. Flow separation characteristics and thrust producing wake profiles are identifie...
A computational analysis of operations in waxy crude oil pipelines Güney, Aylin; Eralp, O. Cahit; Department of Mechanical Engineering (1999)
A computational study of flow entrainment over a stationary/flapping airfoil combination in tandem Tuncer, İsmail Hakkı; Platzer, Max F. (1998-01-01) © 1997, American Institute of Aeronautics and Astronautics, Inc.Unsteady flowfields over a stationary/flapping airfoil combination in tandem are computed using a Reynolds averaged Navier-Stokes solver. The stationary leading airfoil has an experimental profile which promotes flow separation at its trailing edge. The effect of the flapping airfoil on the leading airfoil and the flow reattachment at the trailing edge are investigated by varying the amplitude and frequency of the flapping motion. A single defo...

Citation Formats

M. Uygun and İ. H. Tuncer, “A computational study of subsonic flowfields over a missile configuration,” presented at the AIAA Aerospace Sciences Meeting and Exhibit, (6 - 09 Ocak 1997), Reno, NV, 1997, Accessed: 00, 2021. [Online]. Available: https://hdl.handle.net/11511/77204.