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Computation of airfoil buffet boundariesThe ILLIAC IV computer has been programmed with an implicit, finite-difference code for solving the thin layer compressible Navier-Stokes equation. Results presented for the case of the buffet boundaries of a conventional and a supercritical airfoil section at high Reynolds numbers are found to be in agreement with experimentally determined buffet boundaries, especially at the higher freestream Mach numbers and lower lift coefficients where the onset of unsteady flows is associated with shock wave-induced boundary layer separation.
Document ID
19820027451
Document Type
Reprint (Version printed in journal)
Authors
Levy, L. L., Jr. (NASA Ames Research Center Moffett Field, CA, United States)
Bailey, H. E. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
August 10, 2013
Publication Date
November 1, 1981
Publication Information
Publication: AIAA Journal
Volume: 19
Subject Category
AERODYNAMICS
Distribution Limits
Public
Copyright
Other