0
Research Papers: Flows in Complex Systems

Analysis of the Airfoil Stall With a Modification of Viscous-Inviscid Interaction Concept

[+] Author and Article Information
E. L. Amromin

Mechmath LLC,
Prior Lake, MN 55372

Manuscript received January 11, 2012; final manuscript received February 7, 2013; published online April 8, 2013. Assoc. Editor: Meng Wang.

J. Fluids Eng 135(5), 051105 (Apr 08, 2013) (7 pages) Paper No: FE-12-1008; doi: 10.1115/1.4023784 History: Received January 11, 2012; Revised February 07, 2013

A modification of the viscous-inviscid interaction concept with the employment of coupled vortices around the airfoil wake is introduced for analyzing the airfoil stall. The analyzed flow includes the laminar boundary layers, laminar separation bubble, laminar-turbulent transition zone, turbulent boundary layers, turbulent separation zone, wake, and outer inviscid flow. Integral methods are employed for the boundary layers. The boundaries of separation zones are analyzed as free surfaces, however, their lengths and shapes depend on the Reynolds number. The described modification is validated by a comparison of the numerical results with the previously published experimental data for various airfoils and Reynolds numbers at low Mach numbers. This modification achieves a reasonably good agreement of the computed lift and moment coefficients with their measured values.

Copyright © 2013 by ASME
Your Session has timed out. Please sign back in to continue.

References

Maughmer, M. D., and Coder, J. G., 2010, “Comparisons of Theoretical Methods for Predicting Airfoil Aerodynamic Characteristics,” U.S. Army Research, Development and Engineering Command Technical Report No. 10-D-106.
Martin, P. B., McAlister, K. W., Chandrasekhara, M. S., and Geissler, W., 2003, “Dynamic Stall Measurements and Computations for a VR-12 Airfoil With a Variable Droop Leading Edge,” American Helicopter Society 59th Annual Forum, Phoenix, AZ.
Raiesi, H., Piomelli, U., and Pollard, A., 2011, “Evaluation of Turbulence Models Using Direct Numerical and Large-Eddy Simulation Data,” ASME J. Fluids Eng., 133(2), p. 021203. [CrossRef]
Kwon, O. K., and Pletcher, R. H., 1986, “A Viscous-Inviscid Interaction Procedure—Part 1: Method for Computing Two-Dimensional Incompressible Separated Channel Flows,” ASME J. Fluids Eng., 108(1), pp. 64–70. [CrossRef]
Kwon, O. K., and Pletcher, R. H., 1986, “A Viscous-Inviscid Interaction Procedure—Part 2: Application to Turbulent Flow Over a Rearward-Facing Step,” ASME J. Fluids Eng., 108(1), pp. 71–75. [CrossRef]
Arndt, R. E. A., Amromin, E. L., and Hambleton, W., 2009, “Cavitation Inception in the Wake of a Jet-Driven Body,” ASME J. Fluids Eng., 131(11), p. 111302. [CrossRef]
Fridman, G. M., and Achkinadze, A. S., 2001, “Review of Theoretical Approaches to Nonlinear Supercavitating Flows,” NATO Applied Vehicle Technology Panel, Brussels, Report No. RTO EN-010.
Tulin, M. P., 1964, “Supercavitating Flow—Small Perturbation Theory,” J. Ship Res., 7, pp. 16–37.
Batchelor, G. K., 1970, An Introduction to Fluids Dynamics, Cambridge University Press, Cambridge, England.
Larsson, L., Patel, V. C., and Dyne, G., 1991, “Ship Viscous Flow,” SSPA, Gotenburg, Sweden, 1990 SSPA-CTN-IIHR Workshop Research Report.
Cebeci, T., and Bradshaw, P., 1984, Physical and Computational Aspects of Convective Head Transfer, Springer-Verlag, New York.
Townsend, A. A., 1976, The Structure of Turbulent Boundary Layer, Cambridge University Press, Cambridge, England.
Agarwal, N. K., and Simpson, R. L., 1990, “Backflow Structure of Steady and Unsteady Separating Turbulent Boundary Layer,” AIAA J., 28, pp. 1764–1775. [CrossRef]
Eaton, J. K., and Johnston, J. P., 1981, “A Review of Research on Subsonic Turbulent Flow Reattachment,” AIAA J., 19, pp. 1093–1100. [CrossRef]
Amromin, E. L., 2002, “Scale Effect of Cavitation Inception on a 2D Eppler Hydrofoil,” ASME J. Fluids Eng., 124(1), pp. 186–193. [CrossRef]
Castillo, L., Wang, X., and George, W. K., 2004 “Separation Criterion for Turbulent Boundary Layers via Similarity Analysis,” ASME J. Fluids Eng., 126(3), pp. 297–304. [CrossRef]
Tani, I., Iuchi, M., and Komoda, H., 1961, “Experimental Investigation of Flow Separation Associated With a Step or a Groove,” Aeronautical Research Institute, University of Tokyo, Report No. 364.
Ramamurthy, A. S., Balanchandar, R., and Govinda Ram, H. S., 1991, “Some Characteristics of Flow Past Backward Facing Steps Including Cavitation Effects,” ASME J. Fluids Eng., 113(2), pp. 278–284. [CrossRef]
Mabe, J. H., Calkins, F. T., Wesley, B., Woszidlo, R., Taubert, L., and Wygnanski, I., 2007, “On the Use of Single Dielectric Barrier Discharge Plasma Actuators for Improving the Performance of Airfoils,” AIAA Paper No. 3972.
Beasley, W. D., and McGhee, R. J., 1975, “Experimental and Theoretical Low-Speed Aerodynamic Characteristics of the NACA 651-213, a = 0.5 Airfoil,” NASA Technical Memorandum No. X-3160.
McAlister, K. W., Pucci, S. L., McCroskey, W. J., and Carr, L. W., 1982, “An Experimental Study of Dynamic Stall on Advanced Airfoil Sections Volume. Pressure and Force Data,” USA AVRADCOM Technical Report No. 82-A-8.
Shapiro, A. H., 1953, The Dynamics and Thermodynamics of Compressible Fluid Flow, John Wiley and Sons, New York.
Silberstein, A., 1935, “Scale Effect on Clark Y Airfoil Characteristics From NACA Full-Scale Wind Tunnel Tests,” NACA Report No. 502.

Figures

Grahic Jump Location
Fig. 1

Comparison of the lift and drag prediction with the RANS codes (OVERFLOW and FLUENT) and the viscous-inviscid interaction code (PROFIL07) with the experimental data for airfoils S406 and E387

Grahic Jump Location
Fig. 2

Measured [2] and computed results with a RANS code pressure coefficient Cp on the airfoil at α = 18° and M = 0.3

Grahic Jump Location
Fig. 3

Foil separated flows. (top) Flow around the plate with a constant pressure zone behind it, computed using the Tulin scheme with coupled spiral vortices. (bottom) Suggested scheme of the foil separated flow. The solid line is the foil contour; the dashed line is the computed section of the displacement body surface S that is the effective boundary of the outer inviscid flow. The dotted line shows the upper section of the turbulent separation zone.

Grahic Jump Location
Fig. 4

Scheme of the separated flow behind a step: the dashed line is the displacement body section. The dash-dotted line is the boundary between the inviscid flow and the viscous flow.

Grahic Jump Location
Fig. 5

Effect of dL/L on the computed pressure distribution in comparison with the experimental data [17]

Grahic Jump Location
Fig. 6

Effect of the second vortex location on the intensity of the vortex pair behind the foil S805

Grahic Jump Location
Fig. 7

Computed velocity along S for a NACA foil with the trailing edge separation at Re = 3 × 106

Grahic Jump Location
Fig. 8

Comparison of the computed and measured [14] length of the separation zones behind the backward steps

Grahic Jump Location
Fig. 9

Normalized pressure distribution: comparison between the presented computations and the experimental data [18] for separation zones behind the backward steps in channels. The numbers in the legend show the ratio of H to the channel width.

Grahic Jump Location
Fig. 10

Effects of the Reynolds number and angle of attack on the computed thickness displacement on NACA0021

Grahic Jump Location
Fig. 11

Comparison of the computed and measured [19] points of the boundary layer reattachment behind a laminar bubble over the NACA0021

Grahic Jump Location
Fig. 12

Lift coefficient of the NACA 0021 airfoil; the curves show our computations and the symbols show the experimental data [19]

Grahic Jump Location
Fig. 13

Lift coefficient of the NACA651-213 a = 0.50 airfoil. The curves show the numerical results and the symbols show the experimental data [20]. The numbers in the legend show the values of Re/106.

Grahic Jump Location
Fig. 14

Lift coefficient of the NACA0012 airfoil at Re = 3.9 × 106; the curve shows the numerical results and the symbols show the experimental data [21]

Grahic Jump Location
Fig. 15

Comparison between the computed and the experimental [21] moment coefficient of the airfoil NACA0012 at Re = 3.9 × 106

Grahic Jump Location
Fig. 16

Comparison between the computed (solid line) and measured [23] (rhombs) lift coefficient of the Clark-Y airfoil. At the highest lift Re = 4.2 × 106; Re rises to 4.8 × 106 at low lift. The dashed line shows the ideal fluid asymptote.

Grahic Jump Location
Fig. 17

Computed (solid line) and measured [1] (rhombs) lift coefficient of the S805 airfoil at Re = 106

Tables

Errata

Discussions

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
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
Sign In