Fluid Mechanics of Compressible Dynamic Stall Control Using Dynamically Deforming Airfoils
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Authors
Chandrasekhara, M.S.
Subjects
flow control
adaptive airfoils
dynamic stall
unsteady surface shear stress
adaptive airfoils
dynamic stall
unsteady surface shear stress
Advisors
Date of Issue
2001-12
Date
December 2001
Publisher
Language
Abstract
This report summarizes the key results from the two components of the study: (1) development of the
knowledge and understanding of the fundamental fluid mechanics of the interactions of the unsteady flow
occurring under the influence of the time scales of airfoil reduced frequency and dynamic leading edge
adaptation at different flow conditions; (2) understanding of the role of the surface flow in compressible
dynamic stall onset. For the former, a systematic investigation of the dynamic stall flow (or lack thereof) was
carried out using a dynamically deforming leading edge airfoil, which allowed us to establish the fact there are
some airfoil leading edge geometries that are indeed dynamic stall free. This offers the hope that rotor blade
geometries can be adapted to avoid the destructive dynamic stall effects, while retaining its benefits. In the
latter, 148 surface shear stress sensors were installed on an NACA 0012 airfoil and the flow behavior studied
for various flow conditions, which showed the various stall onset mechanisms discovered earlier and also that
the surface behavior becomes singular prior to stall onset.
Type
Report
Description
Series/Report No
Department
Organization
Naval Postgraduate School (U.S.)
Identifiers
NPS Report Number
Sponsors
U.S. Army Research Office ARO-36477-EG.10
Funder
U.S. Army Research Office ARO-36477-EG.10
Format
41 p.
Citation
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.