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Compressible studies on dynamic stallThe purpose of this work is to investigate the effects of compressibility on the dynamic stall phenomenon by numerical simulation of the unsteady flow. The full two-dimensional unsteady compressible Navier-Stokes equations are solved for flows over oscillating airfoils and airfoils pitching rapidly to high angles of attack. The free-stream speeds vary from low subsonic with mild compressibility effects, to moderate subsonic where strong compressibility effects appear close to the leading edge at high angles of attack. An Alternating Direction Implicit scheme is implemented for the numerical solution with the viscous terms retained in both directions. The numerical results are compared with available experimental data for a Sikorsky airfoil for compressible high Reynolds number flows. There is good agreement between the computed and measured unsteady lift and pitching moment coefficient time histories. The computed high-speed subsonic unsteady results give a good picture of the entire flow field, and the dynamic stall progression in the compressible flow regime. It was observed that compressibility effects are more severe close to the leading edge at moderate angles of attack, and that the dynamic stall vortex appears at lower angles of attack as the free-stream speed increases.
Document ID
19890037649
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Ekaterinaris, J. A.
(NASA Ames Research Center; Sterling Federal Systems, Inc. Moffett Field, CA, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1989
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 89-0024
Accession Number
89A25020
Distribution Limits
Public
Copyright
Other

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