Abstract
Unsteady boundary layer transition on a pitching OA209 airfoil in a wind tunnel was detected by using pressure fluctuation measurement at different oscillation frequency. Thirty Kulite dynamic pressure transducers flush-mounted on the airfoil surface recorded pressure signatures, and root mean square of pressure signatures were calculated. Results indicated that the criterion of transition for static airfoil defined as the peak of root mean square of pressure fluctuation was still suitable for detection of transition on a pitching airfoil. Fixed transition experiment for pitching airfoil was performed to validate the conclusion. Effect of oscillation frequency on transition was investigated. For small reduced frequency, the hysteresis loop is larger near leading edge. With increasing in the oscillation frequencies, the transition was promoted and relaminarization was enhanced.
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References
A. Klein et al., Unsteady criteria for rotor blade airfoil design, 35th European Rotorcraft Forum, Hamburg, Germany (2009).
M. R. Mohaghegh and M. M. Jafarian, Periodic transonic flow simulation using fourier-based algorithm, J. of Mechanical Science and Technology, 28 (10) (2014) 4109–4119.
J. Feng, X. Luo, P. Guo and G. Wu, Influence of tip clearance on pressure fluctuations in an axial flow pump, J. of Mechanical Science and Technology, 30 (4) (2016) 1603–1610.
C. F. Knapp and P. J. Roache, A combined visual and hotwire anemometer investigation of boundary-layer transition, AIAA J., 6 (1) (1968) 29–36.
J. E. Lagraff, Observations of hypersonic boundary-layer transition using hot wire anemometry, AIAA J., 10 (6) (1972) 762–769.
M. Costantini et al., Nonadiabatic surface effects on transition measurements using temperature sensitive paints, AIAA Journal, 53 (5) (2015) 1172–1187.
U. Fey, Y. Egami and C. Klein, Temperature-sensitive paint application in cryogenic wind tunnels: Transition detection at high reynolds numbers and influence of the technique on measured aerodynamic coefficients, 22nd International Congress on Instrumentation in Aerospace Simulation Facilities, California, USA (2007) 304–320.
V. Borovoy et al., Temperature sensitive paint application for investigation of boundary layer transition in shortduration wind tunnels, Progress in Flight Physics, 3 (2012) 15–24.
R. H. M. Giepman, F. F. J. Schrijer and B. W. van Oudheusden, Infrared thermography measurements on a moving boundary-layer transition front in supersonic flow, AIAA J., 53 (7) (2015) 2056–2061.
M. Raffel and C. B. Merz, Differential infrared thermography for unsteady boundary-layer transition measurements, AIAA J., 52 (9) (2014) 2090–2093.
M. Raffel et al., Differential infrared thermography for boundary layer transition detection on pitching rotor blade models, Experiments in Fluids, 56 (2) (2015) 1–13.
C. B. Merz, K. Richter and M. Raffel, Unsteady boundary layer transition measurements by differential infrared thermography, 70th Annual Forum of the American Helicopter Society, Quebec, Canada (2014).
H. Hodson and R. Howell, Unsteady flow: Its role in the low pressure turbine, 9th International Symposium Unsteady Aerodynamics, Aeroacoustics and Aeroelasticity of Turbomachine, Lyon, France (2000).
X. Zhang, M. Ali and S. Steen, Hot-film measurements of boundary layer transition, separation and reattachment on a low-pressure turbine airfoil at low reynolds numbers, 38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, Indiana, USA (2002) 3643–3655.
T. Lee and P. Gerontakos, Investigation of flow over an oscillating airfoil, J. of Fluid Mechanics, 512 (2004) 313–341.
T. Lee and S. Basu, Measurement of unsteady boundary layer developed on an oscillating airfoil using multiple hotfilm sensors, Experiments in Fluids, 25 (2) (1998) 108–117.
K. Richter et al., Experimental investigation of unsteady transition on a pitching rotor blade airfoil, J. of the American Helicopter Society, 59 (1) (2014) 1–12.
D. H. Kim and J. W. Chang, Reynolds number effects on unsteady boundary layer for an oscillating airfoil, 27th AIAA Applied Aerodynamics Conference, San Antonio, Texas, USA (2009) 3501–3513.
A. Haghiri, M. Mani and N. Fallahpour, Unsteady boundary layer measurement on an oscillating (pitching) supercritical airfoil in compressible flow using multiple hot-film sensors, J. of Aerospace Engineering, 229 (10) (2015) 1771–1784.
E. Schülein, H. Rosemann and S. Schaber, Transition detection and skin friction measurements on rotating propeller blades, 28th AIAA Aerodynamic Measurement Technology, Ground Testing and Flight Testing Conference, New Orleans, LA, USA (2012) 3202–3226.
S. M. Batill and T. J. Mueller, Visualization of transition in the flow over an airfoil using the smoke-wire technique, AIAA J., 19 (3) (1981) 340–345.
H. H. Heller, Acoustic technique for detection of flow transition on hypersonic re-entry vehicles, AIAA J., 7 (12) (1969) 2227–2232.
T. L. Lewis and R. D. Banner, Boundary layer transition detection on the x-15 vertical fin using surface-pressurefluctuation measurements, NASA TM X-2466 (1971).
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Recommended by Associate Editor Seongwon Kang
Yongwei Gao received his Bachelor’s in aerodynamics, and Master’s and Ph.D. in fluid dynamics from Northwestern Polytechnical University (NPU) in China. He is a Professor at the school of Aeronautics and head of the laboratory of NF-3 low-speed wind tunnel in NPU. His works focus on experimental fluid dynamics and aero acoustics.
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Gao, Y., Zhu, Q. & Wang, L. Measurement of unsteady transition on a pitching airfoil using dynamic pressure sensors. J Mech Sci Technol 30, 4571–4578 (2016). https://doi.org/10.1007/s12206-016-0928-5
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DOI: https://doi.org/10.1007/s12206-016-0928-5