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Dynamic stall experiments on the NACA 0012 airfoilThe flow over a NACA 0012 airfoil undergoing large oscillations in pitch was experimentally studied at a Reynolds number of and over a range of frequencies and amplitudes. Hot-wire probes and surface-pressure transducers were used to clarify the role of the laminar separation bubble, to delineate the growth and shedding of the stall vortex, and to quantify the resultant aerodynamic loads. In addition to the pressure distributions and normal force and pitching moment data that have often been obtained in previous investigations, estimates of the unsteady drag force during dynamic stall have been derived from the surface pressure measurements. Special characteristics of the pressure response, which are symptomatic of the occurrence and relative severity of moment stall, have also been examined.
Document ID
Document Type
Technical Publication (TP)
Mcalister, K. W.
(NASA Ames Research Center Moffett Field, CA, United States)
Carr, L. W.
(NASA Ames Research Center Moffett Field, CA, United States)
Mccroskey, W. J.
(NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
September 3, 2013
Publication Date
January 1, 1978
Subject Category
Report/Patent Number
Distribution Limits
Work of the US Gov. Public Use Permitted.

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