NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
A numerical study of the unsteady leading edge separation bubble on an oscillating airfoilA preliminary study of the unsteady viscous flow in the region of an airfoil leading edge was performed, in which the interaction between the viscous and inviscid flow fields is neglected. The solution method uses the finite difference form of the governing equations throughout the separated flow field and incorporates a transition model based on the integral turbulence kinetic energy equation. The validity of the numerical procedure is verified by making comparisons with analytical solutions to several test problems, including unsteady flow over a plate oscillating in its own plane. The method was then applied to the problem of unsteady viscous flow over a NACA 0012 airfoil oscillating sinusoidally in pitch. The flow field characteristics were in qualitative agreement with experimental results. The bubble moved forward on the airfoil and decreased in size as incidence was increased. Viscous flow in the leading edge region was found to be quasi-steady, while bubble height varied inversely with Reynolds number.
Document ID
19770053387
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Kreskovsky, J. P.
(United Technologies Research Center East Hartford, CT, United States)
Shamroth, S. J.
(United Technologies Research Center East Hartford, CT, United States)
Briley, W. R.
(United Technologies Research Center East Hartford, Conn., United States)
Date Acquired
August 9, 2013
Publication Date
April 1, 1977
Publication Information
Publication: Computer Methods in Applied Mechanics and Engineering
Volume: 11
Subject Category
Aerodynamics
Accession Number
77A36239
Funding Number(s)
CONTRACT_GRANT: NAS1-11568
Distribution Limits
Public
Copyright
Other

Available Downloads

There are no available downloads for this record.
No Preview Available