Hostname: page-component-cd9895bd7-fscjk Total loading time: 0 Render date: 2024-12-25T06:06:43.260Z Has data issue: false hasContentIssue false
  • English
  • Français

A direct viscid-inviscid interaction scheme for the prediction of two-dimensional aerofoil lift and pitching moment in incompressible flow

Part of: 75 year anniversary of Aeronautical Engineering at Glasgow University

Published online by Cambridge University Press:  04 July 2016

F. N. Coton  and
R. A. McD. Galbraith
F. N. Coton
Affiliation:
Department of Aerospace Engineering, University of Glasgow
R. A. McD. Galbraith
Affiliation:
Department of Aerospace Engineering, University of Glasgow
Get access Rights & Permissions [Opens in a new window]

Summary

This paper presents a method for assessing two-dimensional aerofoil lift and pitching moment characteristics including trailing edge and gross laminar separation. The model used is a direct viscid-inviscid interaction scheme based on a vortex panel method with boundary-layer corrections and an inviscidly modelled wake. The integral boundary-layer methods adopted behave well in the region of separation and thus, good comparisons with measured separation characteristics are obtained. Generally the predictions of lift and pitching moment may be considered to be within the experimental error, but where this is not the case, the applicability of the modelling technique is discussed.

Type
Research Article
Information
The Aeronautical Journal , Volume 93 , Issue 924 , April 1989 , pp. 132 - 140
Copyright
Copyright © Royal Aeronautical Society 1989 

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

1. Liebeck, R. H. Design of subsonic airfoils for high lift, J Aircr, Sept 1978, 15, (9), 547–561.Google Scholar
2. Mcmasters, J. H. and Henderson, M. L. Low-speed single element airfoil synthesis, Tech Soar, 1979, 6, (2), 1–21.Google Scholar
3. Leishman, J. G. and Galbraith, R. A. McD. An Algorithm for the Calculation of the Potential Flow About an Arbitrary Two-Dimensional Aerofoil, Glasgow University Aero Report No. 8102, 1981.Google Scholar
4. Mueller, T. J. Low Reynolds Number Vehicles, AGARDograph No. 288, February 1985.Google Scholar
5. Williams, B. R. The Calculation of Flow About Aerofoils at Low Reynolds Number With Application to Remotely Piloted Vehicles, International Conference on Aerodynamics at Low Reynolds Numbers (104 ˂ Re ˂ 106), London, 1986.Google Scholar
6. Maskew, B., Dvorak, F. A. The prediction of CLmax using a separated flow model, J Am Helicopter Soc, Apr 1978, 23, (2), 2–8.Google Scholar
7. Coton, F. N. and Galbraith, R. A. McD. A Simple Method For The Prediction of Separation Bubble Formation on Aerofoils at Low Reynolds Number, International Conference on Aerodynamics at Low Reynolds Numbers (104 ˂ Re ˂ 106) London, 1986.Google Scholar
8. Horton, H. P. A Semi-Empirical Theory for the Growth and Bursting of Laminar Separation Bubbles’, ARC. C.P. No. 1703, 1969.Google Scholar
9. Leishman, J. G., Galbraith, R. A. McD. and Hanna, J. Modelling of Trailing Edge Separation on Arbitrary Two-Dimensional Aerofoils in Incompressible Flow Using an Inviscid Flow Algorithm, Glasgow University Aero Report No. 8202, 1982.Google Scholar
10. Le Foll, J. A theory of representation of the properties of boundary layers on a plane, In: Proceedings of a Seminar on Advanced Problems in Turbomachinery, V.K.I., 1965.Google Scholar
11. Assassa, G. M. and Papailiou, K. D. An integral method for calculating turbulent boundary layer with separation, Trans ASME, 1979, 100, 110–116.Google Scholar
12. Head, M. R. An Approximate Method for Calculating the Laminar Boundary Layer in Two-Dimensional Incompressible Flow, ARC. R&M No. 3123, 1959.Google Scholar
13. Cebeci, T. and Smith, A.M.O. Analysis of turbulent boundary layers, In: Applied Mathematics and Mechanics, Vol. 15, Academic Press, London, 1974.Google Scholar
14. Coles, D. The Law of the Wake in the Turbulent Boundary Layer,’ CI.T. Report, 1955.Google Scholar
15. Khun, G. D. and Neilsen, J. N. Prediction of turbulent separated boundary layers, AIAA J, 1974, 12, (7), 881–882.Google Scholar
16. Nash, J. F. Turbulent Boundary Layer Behaviour and the Auxiliary Equation, AGARDograph 97, Part 1, 1965, 245–279.Google Scholar
17. Chu, J. and Young, A. D. Measurements in Two-Dimensional Turbulent Boundary Layers, AGARD C.P. No. 168, 1975.Google Scholar
18. Mcghee, R. I. and Beasley, W. D. Low-Speed Aerodynamic Characteristics of a 17-Percent-Thick Airfoil Section Designed for General Aviation Applications, NASA TN D-7428, 1973.Google Scholar
19. Miley, S. J. A Catalog of Low Reynolds Number Airfoil Data for Wind Turbine Applications, Aerospace Engineering Dept., Texas A&M University, 1982.Google Scholar
20. Gleyzes, C., Cousteix, J. and Bonnet, I. L. A calculation method of leading edge separation bubbles. In: Numerical and Physical Aspects of Aerodynamic Flows, Vol II, 1984.Google Scholar
21. Kelling, F. H. Experimental Investigation of a High-Lift Low- Drag Aerofoil, Glasgow University Report No. 6802, 1968.Google Scholar
22. Galbraith, R. A. McD. ‘The Aerodynamic Characteristics of a GU25-5(11)8 Aerofoil for Low Reynolds Numbers, Glasgow University Report No. 8410, 1984.Google Scholar