Numerical studies of unsteady transonic flow over oscillating airfoilA finite difference solution to the Navier-Stokes equations combined with a time varying grid generation technique was used to compute unsteady transonic flow over an oscillating airfoil. These computations were compared with experimental data (obtained at Ames Research Center) which form part of the AGARD standard configuration for aeroelastic analysis. A variety of approximations to the full Navier-Stokes equations was used to determine the effect of frequency, shock wave motion, flow separation, and airfoil geometry on unsteady pressures and overall air loads. Good agreement is shown between experiment and theory with the limiting factor being the lack of a reliable turbulence model for high Reynolds number, unsteady transonic flows.
Document ID
19850016863
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Chyu, W. J. (NASA Ames Research Center Moffett Field, CA, United States)
Davis, S. S. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
August 12, 2013
Publication Date
January 1, 1985
Publication Information
Publication: AGARD Transonic Unsteady Aerodyn. and its Aeroelastic Appl.