Journal of Mechanical Science and Technology

, Volume 33, Issue 1, pp 279–288 | Cite as

Analysis of flow transition and separation on oscillating airfoil by pressure signature

  • Binbin Wei
  • Yongwei GaoEmail author
  • Long Wang
  • Dong Li


To have a better understanding of the unsteady aerodynamic characteristics of the airfoil which play important roles in wind turbine blade design, we investigated the boundary layer transition and separation on oscillating airfoil S809 using pressure signature captured in wind tunnel testing. The developed data processing technique of “sliding window” was applied to get useful transition and separation information. Meanwhile, the hysteresis effects of oscillation frequency on transition and separation were studied. It is found that (1) the root mean square (RMS) of pressure signature can indicate the transition and separation with the dimensionless window width of \(\bar m = 0.0015\) (2) the transitional attack of angle in up stroke is larger than that in down stroke at the state of the relative chord length of x/c ≥ 0.14, while the situation is opposite at the state of the relative chord length of x/c ≤ 0.14; (3) the flow separation is advanced and the reattachment is delayed with the increase of the oscillation frequency, which results in a greater hysteresis effect. The sliding window technique, whose parameters were determined in this paper, is effective for detecting boundary layer transition and separation from pressure signature.


Pressure signature Transition and separation Sliding window Hysteresis effect 


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  1. [1]
    A. Klein et al., Unsteady criteria for rotor blade airfoil design, 35th European Rotorcraft Forum, Hamburg, Germany (2009).Google Scholar
  2. [2]
    L. W. Carr, Progress in analysis and prediction of dynamic stall, J. of Aircraft, 25 (1) (1988) 6–17, Doi: 10.2514/3.45534.CrossRefGoogle Scholar
  3. [3]
    J. Leishman, Validation of approximate indicial aerodynamic functions for two-dimensional subsonic flow, J. of Aircraft, 25 (10) (1988) 914–922, Doi: 10.2514/3.45680.CrossRefGoogle Scholar
  4. [4]
    K. W. Mcalister, O. Lambert and D. Petot, Application of the ONERA model of dynamic stall, NASA TP–2399 (1984).Google Scholar
  5. [5]
    M. Dindar and U. Kaynak, Effect of turbulence modeling on dynamic stall of a NACA0012 airfoil, Aerospace Sciences Meeting and Exhibit (1992).CrossRefGoogle Scholar
  6. [6]
    A. Jameson, Time dependent calculations using multigrid, with applications to unsteady flows past airfoils and wings, Computational Fluid Dynamics Conference (1991) Doi: 10.2514/6.1991–1596.Google Scholar
  7. [7]
    S. Ko and W. J. Mccroskey, Computations of unsteady separating flows over an oscillating airfoil, Aiaa J., 35 (7) (1997) 1235–1238, Doi: 10.2514/2.226.CrossRefGoogle Scholar
  8. [8]
    T. Lee and P. Gerontakos, Investigation of flow over an oscillating airfoil, J. of Fluid Mechanics, 512 (512) (2004) 313–341, Doi: 10.1017/S0022112004009851.zbMATHGoogle Scholar
  9. [9]
    M. Pascazio et al., Unsteady boundary-layer measurement on oscillating airfoils-Transition and separation phenomena in pitching motion, Aerospace Sciences Meeting and Exhibit (1996) Doi: 10.2514/6.1996–35.Google Scholar
  10. [10]
    F. R. Marzabadi and M. R. Soltani, Effect of leading-edge roughness on boundary layer transition of an oscillating airfoil, Scientia Iranica, 20 (3) (2013) 508–515.Google Scholar
  11. [11]
    C. F. Knapp and P. J. Roache, A combined visual and hotwire anemometer investigation of boundary-layer transition, AIAA Journal, 6 (1968) 29–36, Doi 10.2514/3.4437.CrossRefGoogle Scholar
  12. [12]
    J. E. Lagraff, Observations of hypersonic boundary-layer transition using hot wire anemometry, AIAA Journal, 10 (1972) 762–769, Doi: 10.2514/3.50208.CrossRefGoogle Scholar
  13. [13]
    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, Doi: 10.4050/JAHS. 59.012001.CrossRefGoogle Scholar
  14. [14]
    M. Costantini, U. Fey, U. Henne and C. Klein, Nonadiabatic surface effects on transition measurements using temperature-sensitive paints, AIAA J., 53 (2015) 1172–1187, Doi: 10.2514/1.J053155.CrossRefGoogle Scholar
  15. [15]
    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. (2015) 1–5, Doi: 10.2514/1.J053910.Google Scholar
  16. [16]
    E. Schülein, H. Rosemann and S. Schaber, Transition detection and skin friction measurements on rotating propeller blades, Paper AIAA-2012-3202, 28th AIAA Aerodynamic Measurement Technology, Ground Testing and Flight Testing Conference, New Orleans, Louisiana, 25–28 June (2012) Doi: 10.2514/6.2012-3202.CrossRefGoogle Scholar
  17. [17]
    H. H. Heller, Acoustic technique for detection of flow transition on hypersonic re-entry vehicles, AIAA J., 7 (1969) 2227–2232, Doi: 10.2514/3.5520.CrossRefGoogle Scholar
  18. [18]
    T. L. Lewis and R. D. Banner, Boundary layer transition detection on the X-15 vertical fin using surface-pressure-fluctuation measurements, NASA TM X-2466 (1971).Google Scholar
  19. [19]
    Y. Gao, Q. Zhu and L. Wang, Measurement of unsteady transition on a pitching airfoil using dynamic pressure sensors, J. of Mechanical Science and Technology, 30 (10) (2016) 4571–4578, Doi: 10.1007/s12206-016-0928-5.CrossRefGoogle Scholar

Copyright information

© The Korean Society of Mechanical Engineers and Springer-Verlag GmbH Germany, part of Springer Nature 2019

Authors and Affiliations

  1. 1.School of AeronauticsNorthwestern Polytechnical UniversityXi’anChina

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