Separation and transition of flow over a pitching airfoil at transitional Reynolds Number are analyzed experimentally. The method is based on a windowed correlation between hot-film sensor signals taken simultaneously or synchronized based on the airfoil pitch angle. A comparison with large eddy simulation (LES) simulation obtained in the same conditions is presented and discussed. Our results agree very well with the LES data for the separation location during the pitch-up. For the pitch-down, the results show differences with the LES. However, when the LES data are analyzed with the same correlation technique, the results are in a better agreement.
Issue Section:
Technical Brief
References
1.
Mueller
, T.
, 1985
, “Low Reynolds Number Vehicles
,” NATO Advisory Group for Aerospace Research and Development, Neuilly sur Seine, France, Technical Report No. AGARD-AG 288.2.
Gad-el Hak
, M.
, 1990
, “Control of Low Airfoil Aerodynamics
,” AIAA J.
, 28
(9
), pp. 1537
–1552
.3.
Poirel
, D.
, Harris
, Y.
, and Benaissa
, A.
, 2008
, “Self-Sustained Aeroelastic Oscillations of a NACA0012 Airfoil at Low-to-Moderate Reynolds Numbers
,” J. Fluids Struct.
, 24
(5
), pp. 700
–719
.4.
Yuan
, W.
, Poirel
, D.
, Wang
, B.
, and Khalid
, M.
, 2012
, “Simulations of Airfoil Limit-Cycle Oscillations at Transitional Reynolds Numbers
,” AIAA
Paper No. 2012-0041.5.
Poirel
, D.
, Metivier
, V.
, and Dumas
, G.
, 2011
, “Computational Aeroelastic Simulations of Self-Sustained Pitch Oscillations of a NACA0012 at Transitional Reynolds Numbers
,” J. Fluids Struct.
, 27
(8
), pp. 1262
–1277
.6.
Rudmin
, D.
, 2012
, “Detection of Laminar Flow Separation and Transition on a Pitching NACA0012 Airfoil
,” Master's thesis, Mechanical and Aerospace Engineering, Royal Military College of Canada, Kingston, ON, Canada.7.
Rudmin
, D.
, Benaissa
, A.
, and Poirel
, D.
, 2013
, “Detection of Laminar Flow Separation and Transition on a NACA0012 Airfoil Using Surface Hot-Films
,” ASME J. Fluids Eng.
, 135
(10
), p. 101104
.8.
Lee
, T.
, and Basu
, S.
, 1998
, “Measurement of Unsteady Boundary Layer Developed on an Oscillating Airfoil Using Multiple Hot-Film Sensors
,” Exp. Fluids
, 25
(2
), pp. 108
–117
.9.
Stack
, J.
, and Mangalam
, S.
, 1989
, “Method and Apparatus for Detecting Laminar Flow Separation and Reattachment
,” U.S. Patent No. 4-848-153.10.
Desgeorges
, O.
, Lee
, T.
, and Kafyeke
, J.
, 2002
, “Multiple Hot-Film Sensor Array Calibration and Skin Friction Measurements,” Exp. Fluids
, 32
(1
), pp. 37
–43
.11.
Alfredsson
, P.
, Johansson
, A.
, Haritonidis
, J.
, and Eckelmann
, H.
, 1988
, “The Fluctuating Wall-Shear Stress and the Velocity Field in the Viscous Sublayer
,” Phys. Fluids
, 31
(5
), p. 1026
.12.
Stack
, J.
, Mangalam
, S.
, and Berry
, S.
, 1987
, “A Unique Measurement Technique to Study Laminar-Separation Bubble Characteristics on an Airfoil
,” AIAA
Paper No. 87-1271.13.
Lee
, T.
, and Gerontakos
, P.
, 2004
, “Investigation of Flow Over an Oscillating Airfoil
,” J. Fluid Mech.
, 512
(1
), pp. 313
–341
.14.
Collin
, X.
, 2007
, “Etude de l'ecoulement a faibles nombres de Reynolds autour d'une aile en oscillations aeroelastiques auto-entretenues
,” Master's thesis, Mechanical and Aerospace Engineering, Royal Military College of Canada, Kingston, ON, Canada.15.
Yuan
, W.
, Poirel
, D.
, and Wang
, B.
, 2013
, “Simulations of Pitch-Heave Limit Cycle Oscillations at a Transitional Reynolds Number
,” AIAA J.
, 51
(7
), pp. 1716
–1732
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