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ADDITIONAL TECHNICAL PAPERS

Reduced-Order Modeling of Unsteady Flows About Complex Configurations Using the Boundary Element Method

[+] Author and Article Information
V. Esfahanian, M. Behbahani-nejad

Department of Mechanical Engineering, University of Tehran, North Amin Abad Avenue, Tehran, Iran

J. Fluids Eng 124(4), 988-993 (Dec 04, 2002) (6 pages) doi:10.1115/1.1511166 History: Received January 11, 2002; Revised May 03, 2002; Online December 04, 2002
Copyright © 2002 by ASME
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References

Hall,  K. C., 1994, “Eigenanalysis of Unsteady Flows About Airfoils, Cascades, and Wings,” AIAA J., 32, pp. 2426–2432.
Romanowski, M. C., and Dowell, E. H., 1996, “Reduced Order Euler Equations for Unsteady Aerodynamic Flows: Numerical Techniques,” AIAA Paper No. 96-0528.
Florea,  R., Hall,  K. C., and Cizmas,  P. G., 1998, “Reduced-Order Modeling of Unsteady Viscous Flow in a Compressor Cascade,” AIAA J., 36, pp. 1039–1048.
Dowell,  E. H., Hall,  K. C., and Romanowski,  M. C., 1997, “Eigenmode Analysis in Unsteady Aerodynamics: Reduced Order Models,” Appl. Mech. Rev., 50(6), pp. 371–385.
IMSL Library Reference Manual, 1980, IMSL LIB-0008.
Rajakumar,  C., and Rogers,  C. R., 1991, “The Lanczos Algorithm Applied to Unsymmetric Generalized Eigenvalue Problem,” Int. J. Numer. Methods Eng., 32, pp. 1009–1026.
Katz, J., and Plotkin, A., 1991, Low-Speed Aerodynamics from Wing Theory to Panel Methods, McGraw-Hill, New York.
Morino,  L., Chen,  L. T., and Susiu,  E. O., 1975, “Steady and Oscillatory Subsonic and Supersonic Aerodynamics around Complex Configurations,” AIAA J., 13, pp. 368–374.
Heeg, J., and Dowell, E. H., 1999, “Aerodynamic and Aeroelastic Insights Using Eigenanalysis,” AIAA Paper No. 99-1473.
Katz,  J., and Maskew,  B., 1988, “Unsteady Low-Speed Aerodynamic Model for Complete Aircraft Configurations,” J. Aircr., 25(4), pp. 302–310.
Romanowski, M. C., 1995, “Using Fluid Eigenmodes to Develop Euler Based Reduced Order Unsteady Aerodynamic and Aeroelastic Models,” PhD. thesis, Duke University, Durham, NC.

Figures

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Potential flow model of a body submerged in fluid
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Eigenvalues of boundary element model of unsteady flow about a NACA 0012 airfoil
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Lift and pitching moment loops for the pitch oscillation of a NACA 0012 airfoil
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Lift response versus time for a NACA 0012 airfoil at Mach 0.5 oscillating at ±1 degree about zero angle of attack with k=0.10
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Lift response vs time for a NACA 0012 airfoil at Mach 0.5 oscillating at ±1 degree about zero angle of attack with k=0.40
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Geometry of the three-dimensional wing and the wake in heaving oscillation (half of the wing is shown)
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Eigenvalues of boundary element model of unsteady flow about a rectangular wing with NACA 0012 section
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Periodic lift variation during heaving oscillation with k=0.10, of a rectangular wing with NACA 0012 section
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Periodic lift variation during heaving oscillation with k=0.30, of a rectangular wing with NACA 0012 section
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Dimensions of the wing-body combination
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Geometry of the wing-body combination and its wake in heaving oscillation
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Eigenvalues of boundary element model of unsteady flow about the wing-body configuration
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Periodic lift variation during heaving oscillation with k=0.30, of the wing-body configuration

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