Flow Visualization by Laser Sheet
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Authors
Hebbar, S.K.
Chandrasekhara, M.S.
Chlebanowski, J.S.
Subjects
Advisors
Date of Issue
1989-08
Date
Publisher
Language
Abstract
Compressibility effects on the dynamic stall of a
NACA 0012 airfoil undergoing sinusoidal oscillatory
motion were studied using a stroboscopic schlieren
system. Schlieren pictures and some quantitative
data derived from them are presented and show the
influence of free-stream Mach number and reduced
frequency on the dynamic-stall vortex. This study
shows that a dynamic stall vortex always forms near
the leading edge and convects on the^ airfoil upper
surface at approximately 0.3 times the free stream
velocity for all cases studied. The results also demonstrate
that initiation of the the dynamic stall vortex
is delayed to higher angles of attack with increased
reduced frequency, but that dynamic stall occurs at
lower angles of incidence with increasing Mach numbers.
Type
Description
Proc. 4th Asian Congress of Fluid Mechanics, Hong Kong, Aug. 1989.
Series/Report No
Department
Organization
Identifiers
NPS Report Number
Sponsors
Funder
ARO-MIPR-137-86
AFOSR-MIPR-88
NAVAIR
AFOSR-MIPR-88
NAVAIR
Format
Citation
S.K. Hebbar, M.S. Chandrasekhara and J.S. Chlebanowski, "Flow Visualization by Laser Sheet", Proc. 4th Asian Congress of Fluid Mechanics, Hong Kong, Aug. 1989.
Distribution Statement
Rights
This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.