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Predicted and experimental steady and unsteady transonic flows about a biconvex airfoilResults of computer code time dependent solutions of the two dimensional compressible Navier-Stokes equations and the results of independent experiments are compared to verify the Mach number range for instabilities in the transonic flow field about a 14 percent thick biconvex airfoil at an angle of attack of 0 deg and a Reynolds number of 7 million. The experiments were conducted in a transonic, slotted wall wind tunnel. The computer code included an algebraic eddy viscosity turbulence model developed for steady flows, and all computations were made using free flight boundary conditions. All of the features documented experimentally for both steady and unsteady flows were predicted qualitatively; even with the above simplifications, the predictions were, on the whole, in good quantitative agreement with experiment. In particular, predicted time histories of shock wave position, surface pressures, lift, and pitching moment were found to be in very good agreement with experiment for an unsteady flow. Depending upon the free stream Mach number for steady flows, the surface pressure downstream of the shock wave or the shock wave location was not well predicted.
Document ID
19810010216
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Levy, L. L., Jr. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
September 4, 2013
Publication Date
February 1, 1981
Subject Category
Numerical Analysis
Report/Patent Number
NASA-TM-81262
A-8457
Accession Number
81N18742
Funding Number(s)
PROJECT: RTOP 505-31-11-05-00-21
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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