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Unsteady N-S Calculations for NACA0012 Airfoil at High Angle of Attack Oscillating

Song, W.P. and Pahlke, K. (1996) Unsteady N-S Calculations for NACA0012 Airfoil at High Angle of Attack Oscillating. DLR-Interner Bericht. 129-96/18, 39 S.

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Abstract

The existing DLR code using the dual time method for solving the unsteady two-dimensional Navier-Stokes equations is improved to calculate the unsteady motion of NACA0012 airfoil oscillating at high angle of attack. Results obtained from single grid and multigrid calculations are given and compared with the experimental data. The influence of the magnitude of physical time step, the inner iteration tolerance, the artifical dissipative terms, the different farfield boundary treatments, the transition position and the correction smoothing coefficient, the cycle type and the number of levels in multigrid calculation is discussed in this report.

Document Type:Monograph (DLR-Interner Bericht)
Additional Information: LIDO-Berichtsjahr=1996,
Title:Unsteady N-S Calculations for NACA0012 Airfoil at High Angle of Attack Oscillating
Authors:
AuthorsInstitution or Email of Authors
Song, W.P.UNSPECIFIED
Pahlke, K.UNSPECIFIED
Date:1996
Number of Pages:39
Status:Published
Keywords:Instationäre Strömung, Navier-Stokes Gleichungen, reibungsbehaftete Strömung, oszillierendes Profil, Ablösung der Strömung, Dynamic Stall
HGF - Research field:UNSPECIFIED
HGF - Program:Aeronautics
HGF - Program Themes:other
DLR - Research area:UNSPECIFIED
DLR - Program:L DT - Drehflüglertechnologien
DLR - Research theme (Project):L - The Quiet and Comfortable Rotorcraft
Location: Köln-Porz , Braunschweig , Göttingen
Institutes and Institutions:Institute of Aerodynamics and Flow Technology > Institut für Entwurfsaerodynamik
Deposited By: elib DLR-Beauftragter
Deposited On:03 Apr 2006
Last Modified:27 Apr 2009 10:06

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