Boundary layers on oscillating airfoilsA two-point finite-difference unsteady laminar and turbulent boundary-layer computational method has been used to investigate the properties of the flow around an airfoil (NACA 0012) oscillating through angles of attack up to 18 degrees, and for reduced frequencies of 0.01 and 0.20. The unsteady potential flow was determined using the method of Geissler. The influence of transition location on stall behavior has been investigated, using both experimentally determined transition information, and transition located at the pressure peak; the results show the need for viscous-inviscid interaction in future computations of such flows.
Document ID
19850060822
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Carr, L. W. (NASA Ames Research Center Moffett Field, CA, United States)
Cebeci, T. (California State University Long Beach, CA, United States)
Date Acquired
August 12, 2013
Publication Date
January 1, 1985
Subject Category
Aerodynamics
Meeting Information
Meeting: Symposium on Numerical and Physical Aspects of Aerodynamic Flows