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The computation of the post-stall behavior of a circulation controlled airfoilThe physics of the circulation controlled airfoil is complex and poorly understood, particularly with regards to jet stall, which is the eventual breakdown of lift augmentation by the jet at some sufficiently high blowing rate. The present paper describes the numerical simulation of stalled and unstalled flows over a two-dimensional circulation controlled airfoil using a fully implicit Navier-Stokes code, and the comparison with experimental results. Mach numbers of 0.3 and 0.5 and jet total to freestream pressure ratios of 1.4 and 1.8 are investigated. The Baldwin-Lomax and k-epsilon turbulence models are used, each modified to include the effect of strong streamline curvature. The numerical solutions of the post-stall circulation controlled airfoil show a highly regular unsteady periodic flowfield. This is the result of an alternation between adverse pressure gradient and shock induced separation of the boundary layer on the airfoil trailing edge.
Document ID
19930038628
Document Type
Conference Paper
Authors
Linton, Samuel W. (Stanford Univ. CA, United States)
Date Acquired
August 16, 2013
Publication Date
January 1, 1993
Subject Category
AERODYNAMICS
Report/Patent Number
AIAA PAPER 93-0207
Meeting Information
AIAA, Aerospace Sciences Meeting and Exhibit(Reno, NV)
Funding Number(s)
CONTRACT_GRANT: NCA2-259
Distribution Limits
Public
Copyright
Other