0
Journal of Fluids Engineering | Volume 137 | Issue 5 | research-article
Research Papers: Flows in Complex Systems

Surface Pressures Developed on an Airfoil Undergoing Heaving and Pitching Motion

[+] Author and Article Information
T. Lee

Department of Mechanical Engineering,
McGill University,
Montreal, QC H3A 2K6, Canada
e-mail: tim.lee@mcgill.ca

Y. Y. Su

Department of Mechanical Engineering,
McGill University,
Montreal, QC H3A 2K6, Canada

1Corresponding author.

Contributed by the Fluids Engineering Division of ASME for publication in the JOURNAL OF FLUIDS ENGINEERING. Manuscript received July 16, 2014; final manuscript received December 15, 2014; published online February 2, 2015. Assoc. Editor: Kwang-Yong Kim.

J. Fluids Eng 137(5), 051105 (May 01, 2015) (11 pages) Paper No: FE-14-1384; doi: 10.1115/1.4029443 History: Received July 16, 2014; Revised December 15, 2014; Online February 02, 2015
Article
References
Figures
Tables
Citing Articles

The surface pressure distributions and flow patterns developed on and around a NACA 0012 airfoil undergoing heaving and pitching were investigated at Re = 3.6 × 104. Despite extensive investigations conducted by researchers elsewhere, the surface pressure measurements are, however, not readily available in the open archives, which are of importance not only in understanding the unsteady-airfoil boundary-layer flow but also for computational fluid dynamics (CFD) validation. Nevertheless, the results show that the behavior of the surface pressure distribution and the flow pattern of pure heaving closely resembled those of pure pitching. For combined heaving and pitching, the critical aerodynamic values (such as dynamic Cl,max, peak negative Cm, Cl-hysteresis and torsional damping) always exhibited a maximum value at phase shift ϕ = 0 deg. More interestingly, the ϕ = 180 deg phase shift produced a virtually unchanged surface pressure distribution over an entire combined motion cycle.
FIGURES IN THIS ARTICLE
<>
Copyright © 2015 by ASME
Your Session has timed out. Please sign back in to continue.

References

1
Shyy, W., Aono, H., Chimakurthi, S. K., Trizila, P., Kang, C.-K., Cesnik, C. E. S., and Liu, H., 2010, “Recent Progress in Flapping Wing Aerodynamics and Aeroelasticity,” Prog. Aeronaut. Sci., 46(7), pp. 284–327. [CrossRef]
2
McCroskey, W. J., McAlister, K. W., Carr, L. W., Pucci, S. L., Lamber, O., and Indergrand, R. F., 1981, “Dynamic Stall on Advanced Airfoil Sections,” J. Am. Helicopter Soc., 26(3), pp. 40–50. [CrossRef]
3
McCroskey, W. J., 1982, “Unsteady Airfoils,” Annu. Rev. Fluid Mech., 14, pp. 285–311. [CrossRef]
4
Koochesfahani, M. M., 1989, “Vortical Patterns in the Wake of an Oscillating Airfoil,” AIAA J., 27(9), pp. 1200–1205. [CrossRef]
5
Panda, J., and Zaman, K. B. M. Q., 1994, “Experimental Investigation of the Flowfield on an Oscillating Airfoil and Estimation of Lift From Wake Surveys,” J. Fluid Mech., 265, pp. 65–95. [CrossRef]
6
Lee, T., and Gerontakos, P., 2004, “Investigation of Flow Over an Oscillating Airfoil,” J. Fluid Mech., 512, pp. 313–341. [CrossRef]
7
Gerontakos, P., and Lee, T., 2008, “PIV Study of Flow Around Unsteady Airfoil With Dynamic Trailing-Edge Flap Deflection,” Exp. Fluids, 45(6), pp. 955–972. [CrossRef]
8
Amiralaei, M. R., Alighanbari, H., and Hashemi, S. M., 2011, “Flow Field Characteristics Study of a Flapping Airfoil Using Computational Fluid Dynamics,” J. Fluids Struct., 27(7), pp. 1068–1085. [CrossRef]
9
Gharali, K., and Johnson, D. A., 2013, “Dynamic Stall Simulation of a Pitching Airfoil Under Unsteady Freestream Velocity,” J. Fluids Struct., 42, pp. 228–244. [CrossRef]
10
Lu, K., Xie, Y. H., and Zhang, D., 2013, “Numerical Study of Large Amplitude, Nonsinusoidal Motion and Camber Effects on Pitching Airfoil Propulsion,” J. Fluids Struct., 36, pp. 184–194. [CrossRef]
11
Freymuth, P., 1990, “Thrust Generation by an Airfoil in Hover Modes,” Exp. Fluids, 9(1–2), pp. 17–24. [CrossRef]
12
Jones, K. D., Dohring, C. M., and Platzer, M. F., 1998, “Experimental and Computational Investigation of the Knoller–Betz Effect,” AIAA J., 36(7), pp. 1240–1246. [CrossRef]
13
Lai, J. C. S., and Platzer, M. F., 1999, “Jet Characteristics of a Plunging Airfoil,” AIAA J., 37(12), pp. 1529–1537. [CrossRef]
14
Young, J., and Lai, J. C. S., 2004, “Oscillation Frequency and Amplitude Effects on the Wake of a Plunging Airfoil,” AIAA J., 42(10), pp. 2042–2052. [CrossRef]
15
Visbal, M., Yilmaz, T. O., and Rockwell, D., 2013, “Three-Dimensional Vortex Formation on a Heaving Low-Aspect-Ratio Wing: Computations and Experiments,” J. Fluids Struct., 38, pp. 58–76. [CrossRef]
16
Ellington, C. P., van den Berg, C., Willmott, A. P., and Thomas, A. L. R., 1996, “Leading-Edge Vortices in Insect Flight,” Nature, 384(6610), pp. 626–630. [CrossRef]
17
Anderson, J. M., Streitlien, K., Barrett, D. S., and Triantafyllou, M. S., 1998, “Oscillating Foils of High Propulsive Efficiency,” J. Fluid Mech., 360, pp. 41–72. [CrossRef]
18
Read, D. A., Hover, F. S., and Triantafyllou, M. S., 2003, “Forces on Oscillating Foils for Propulsion and Maneuvering,” J. Fluids Struct., 17(1), pp. 163–183. [CrossRef]
19
Young, J., and Lai, J. C. S., 2007, “Mechanisms Influencing the Efficiency of Oscillating Airfoil Propulsion,” AIAA J., 45(7), pp. 1695–1702. [CrossRef]
20
Ashraf, M. A., Young, J., and Lai, J. C. S., 2011, “Reynolds Number, Thickness and Camber Effects on Flapping Airfoil Propulsion,” J. Fluids Struct., 27(2), pp. 145–160. [CrossRef]
21
Amiralaei, M. R., Alighanbari, H., and Hashemi, S. M., 2010, “An Investigation Into the Effects of Unsteady Parameters on the Aerodynamics of a Low Reynolds Number Pitching Airfoil,” J. Fluids Struct., 26(6), pp. 979–993. [CrossRef]
22
Kinsey, T., and Dumas, G., 2012, “Three-Dimensional Effects on an Oscillating-Foil Hydrokinetic Turbine,” ASME J. Fluids Eng., 134(7), p. 071105. [CrossRef]
23
Baik, Y. S., and Bernal, L. P., 2012, “Experimental Study of Pitching and Plunging Airfoils at Low Reynolds Numbers,” Exp. Fluids, 53(6), pp. 1979–1992. [CrossRef]
24
Chen, S. H., and Ho, C. M., 1987, “Near Wake of an Unsteady Symmetric Airfoil,” J. Fluids Struct., 1(2), pp. 151–164. [CrossRef]
25
Rennie, R., and Jumper, E. J., 1996, “Experimental Measurements of Dynamic Control Surface Effectiveness,” J. Aircr., 33(5), pp. 880–887. [CrossRef]
26
Moffat, R. J., 1988, “Describing the Uncertainties in Experimental Results,” Exp. Therm. Fluid Sci., 1(1), pp. 3–17. [CrossRef]
27
Ericsson, L. E., and Reding, J. P., 1988, “Fluid Mechanics of Dynamic Stall. Part I: Unsteady Flow Concepts,” J. Fluids Struct., 2(1), pp. 1–33. [CrossRef]
28
Leishman, J. G., 2002, Principles of Helicopter Aerodynamics, Cambridge University Press, New York, pp. 379–389.

Figures

Grahic Jump Location
Fig. 1

Experimental setup and airfoil model. (a) Schematics of airfoil heaving and pitching mechanism, (b) input and output signals of heaving and pitching, (c) heaving and pitching motion profiles at selected ϕ for αo = 10 deg and Δα = 6 deg, and (d) pressure orifice locations

+Experimental setup and airfoil model. (a) Schematics of airfoil heaving and pitching mechanism, (b) input and output signals of heaving and pitching, (c) heaving and pitching motion profiles at selected ϕ for αo = 10 deg and Δα = 6 deg, and (d) pressure orifice locations
View Large  |  Save Figure  |  Download Slide (.ppt)
Experimental setup and airfoil model. (a) Schematics of airfoil heaving and pitching mechanism, (b) input and output signals of heaving and pitching, (c) heaving and pitching motion profiles at selected ϕ for αo = 10 deg and Δα = 6 deg, and (d) pressure orifice locations
Grahic Jump Location
Fig. 2

Smoke-flow patterns for αo = 10 deg and Δα = 6 deg at selected α, t/T and ϕ. αu and αd denote angles during pitch-up and pitch-down, respectively

+Smoke-flow patterns for αo = 10 deg and Δα = 6 deg at selected α, t/T and ϕ. αu and αd denote angles during pitch-up and pitch-down, respectively
View Large  |  Save Figure  |  Download Slide (.ppt)
Smoke-flow patterns for αo = 10 deg and Δα = 6 deg at selected α, t/T and ϕ. αu and αd denote angles during pitch-up and pitch-down, respectively
Grahic Jump Location
Fig. 3

Smoke-flow patterns of the static airfoil at selected α: (a) α = 6 deg, (b) α = 8 deg, (c) α = 10 deg, (d) α = 12 deg, (e) α = 14 deg, and (f) α = 16 deg

+Smoke-flow patterns of the static airfoil at selected α: (a) α = 6 deg, (b) α = 8 deg, (c) α = 10 deg, (d) α = 12 deg, (e) α = 14 deg, and (f) α = 16 deg
View Large  |  Save Figure  |  Download Slide (.ppt)
Smoke-flow patterns of the static airfoil at selected α: (a) α = 6 deg, (b) α = 8 deg, (c) α = 10 deg, (d) α = 12 deg, (e) α = 14 deg, and (f) α = 16 deg
Grahic Jump Location
Fig. 4

Cp distributions of pure heaving, pure pitching, and combined motion with ϕ = 0 deg for αo = 10 deg and Δα = 6 deg. (a) t/T = 0.23, (b) t/T = 0.27, (c) t/T = 0.37, (d) t/T = 0.45, (e) t/T = 0.48, (f) t/T = 0.50, (g) t/T = 0.57, (h) t/T = 0.66, and (i) t/T = 0.75.

+Cp distributions of pure heaving, pure pitching, and combined motion with ϕ = 0 deg for αo = 10 deg and Δα = 6 deg. (a) t/T = 0.23, (b) t/T = 0.27, (c) t/T = 0.37, (d) t/T = 0.45, (e) t/T = 0.48, (f) t/T = 0.50, (g) t/T = 0.57, (h) t/T = 0.66, and (i) t/T = 0.75.
View Large  |  Save Figure  |  Download Slide (.ppt)
Cp distributions of pure heaving, pure pitching, and combined motion with ϕ = 0 deg for αo = 10 deg and Δα = 6 deg. (a) t/T = 0.23, (b) t/T = 0.27, (c) t/T = 0.37, (d) t/T = 0.45, (e) t/T = 0.48, (f) t/T = 0.50, (g) t/T = 0.57, (h) t/T = 0.66, and (i) t/T = 0.75.
Grahic Jump Location
Fig. 5

Dynamic-Cl and -Cm loops for pure heaving and pure pitching. Solid lines and symbols denote upstroke. Dashed lines and open symbols denote downstroke.

+Dynamic-Cl and -Cm loops for pure heaving and pure pitching. Solid lines and symbols denote upstroke. Dashed lines and open symbols denote downstroke.
View Large  |  Save Figure  |  Download Slide (.ppt)
Dynamic-Cl and -Cm loops for pure heaving and pure pitching. Solid lines and symbols denote upstroke. Dashed lines and open symbols denote downstroke.
Grahic Jump Location
Fig. 6

Spatial-temporal Cp representation for αo = 10 deg and Δα = 6 deg. (a) Pure heave αo = 10 deg, (b) pure pitch αo = 10 deg, Δα = 6 deg, (c) ϕ = 0 deg, (d) ϕ = 90 deg, (e) ϕ = 180 deg, and (f) ϕ = 270 deg.

+Spatial-temporal Cp representation for αo = 10 deg and Δα = 6 deg. (a) Pure heave αo = 10 deg, (b) pure pitch αo = 10 deg, Δα = 6 deg, (c) ϕ = 0 deg, (d) ϕ = 90 deg, (e) ϕ = 180 deg, and (f) ϕ = 270 deg.
View Large  |  Save Figure  |  Download Slide (.ppt)
Spatial-temporal Cp representation for αo = 10 deg and Δα = 6 deg. (a) Pure heave αo = 10 deg, (b) pure pitch αo = 10 deg, Δα = 6 deg, (c) ϕ = 0 deg, (d) ϕ = 90 deg, (e) ϕ = 180 deg, and (f) ϕ = 270 deg.
Grahic Jump Location
Fig. 7

Impact of ϕ on dynamic-Cl and Cm loops for αo = 10 deg, 8 deg and 5 deg with fixed Δα = 6 deg. Solid circles and stars denote start of upstroke and beginning of downstroke.

+Impact of ϕ on dynamic-Cl and Cm loops for αo = 10 deg, 8 deg and 5 deg with fixed Δα = 6 deg. Solid circles and stars denote start of upstroke and beginning of downstroke.
View Large  |  Save Figure  |  Download Slide (.ppt)
Impact of ϕ on dynamic-Cl and Cm loops for αo = 10 deg, 8 deg and 5 deg with fixed Δα = 6 deg. Solid circles and stars denote start of upstroke and beginning of downstroke.
Grahic Jump Location
Fig. 8

Cp distribution for αo = 10 deg and Δα = 6 deg with ϕ = 90 deg, 180 deg, and 270 deg. The pure pitch distributions are shifted by a phase equivalent to ϕ. ϕ = 90 deg: (a) t/T = 0.27, (b) t/T = 0.37, (c) t/T = 0.50, (d) t/T = 0.66, and (e) t/T = 0.75; ϕ = 180 deg (f) t/T = 0.27, (g) t/T = 0.37, (h) t/T = 0.50, (i) t/T = 0.66, and (j) t/T = 0.88; and ϕ = 270 deg (k) t/T = 0.23, (l) t/T = 0.27, (m) t/T = 0.37, (n) t/T = 0.50, and (o) t/T = 0.66.

+Cp distribution for αo = 10 deg and Δα = 6 deg with ϕ = 90 deg, 180 deg, and 270 deg. The pure pitch distributions are shifted by a phase equivalent to ϕ. ϕ = 90 deg: (a) t/T = 0.27, (b) t/T = 0.37, (c) t/T = 0.50, (d) t/T = 0.66, and (e) t/T = 0.75; ϕ = 180 deg (f) t/T = 0.27, (g) t/T = 0.37, (h) t/T = 0.50, (i) t/T = 0.66, and (j) t/T = 0.88; and ϕ = 270 deg (k) t/T = 0.23, (l) t/T = 0.27, (m) t/T = 0.37, (n) t/T = 0.50, and (o) t/T = 0.66.
View Large  |  Save Figure  |  Download Slide (.ppt)
Cp distribution for αo = 10 deg and Δα = 6 deg with ϕ = 90 deg, 180 deg, and 270 deg. The pure pitch distributions are shifted by a phase equivalent to ϕ. ϕ = 90 deg: (a) t/T = 0.27, (b) t/T = 0.37, (c) t/T = 0.50, (d) t/T = 0.66, and (e) t/T = 0.75; ϕ = 180 deg (f) t/T = 0.27, (g) t/T = 0.37, (h) t/T = 0.50, (i) t/T = 0.66, and (j) t/T = 0.88; and ϕ = 270 deg (k) t/T = 0.23, (l) t/T = 0.27, (m) t/T = 0.37, (n) t/T = 0.50, and (o) t/T = 0.66.
Grahic Jump Location
Fig. 9

Impact of ϕ on critical aerodynamic values

+Impact of ϕ on critical aerodynamic values
View Large  |  Save Figure  |  Download Slide (.ppt)
Impact of ϕ on critical aerodynamic values
Grahic Jump Location
Fig. 10

Spatial-temporal Cp representation for αo = 5 deg and Δα = 6 deg. (a) Pure heave αo = 5 deg, (b) pure pitch αo = 5 deg, Δα = 6 deg, (c) ϕ = 0 deg, (d) ϕ = 90 deg, (e) ϕ = 180 deg, and (f) ϕ = 270 deg.

+Spatial-temporal Cp representation for αo = 5 deg and Δα = 6 deg. (a) Pure heave αo = 5 deg, (b) pure pitch αo = 5 deg, Δα = 6 deg, (c) ϕ = 0 deg, (d) ϕ = 90 deg, (e) ϕ = 180 deg, and (f) ϕ = 270 deg.
View Large  |  Save Figure  |  Download Slide (.ppt)
Spatial-temporal Cp representation for αo = 5 deg and Δα = 6 deg. (a) Pure heave αo = 5 deg, (b) pure pitch αo = 5 deg, Δα = 6 deg, (c) ϕ = 0 deg, (d) ϕ = 90 deg, (e) ϕ = 180 deg, and (f) ϕ = 270 deg.

Tables

Errata

Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Interline Power Flow Controller and Impact on ATC Improvement
International Conference on Software Technology and Engineering, 3rd (ICSTE 2011)
Cubic Lattice Structured Multi Agent Based PSO Approach for Optimal Power Flows with Security Constraints
International Conference on Software Technology and Engineering, 3rd (ICSTE 2011)
Optimal Design of a Power Electronic System for Efficient and Reliable Power Flow in Distributed Wind Energy Based Power Systems
International Conference on Software Technology and Engineering, 3rd (ICSTE 2011)
Keeping a Cool Head
Hot Air Rises and Heat Sinks> Chapter 11
Turbulence-Induced Vibration in Parallel Flow
Flow Induced Vibration of Power and Process Plant Components> Chapter 8
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
This site uses cookies. By continuing to use our website, you are agreeing to our privacy policy. | Accept
Sign In