Hostname: page-component-cd9895bd7-q99xh Total loading time: 0 Render date: 2024-12-28T20:21:55.219Z Has data issue: false hasContentIssue false
  • English
  • Français

Part VI: The rapid deployment of a spoiler on a two-dimensional aerofoil

Published online by Cambridge University Press:  04 July 2016

Get access Rights & Permissions [Opens in a new window]

Summary

A method based on the shedding and convecting of discrete vortices has been developed to calculate the transient loading on an aerofoil-spoiler configuration when the spoiler is suddenly deployed to a particular angle. An innovation in the method is the introduction of Kutta conditions at the separation points.

Although the variation of CL with time is highly irregular, qualitative trends can be deduced. For a range of aerofoil angle of incidence and spoiler angle deployment adverse lift effects (ie, when the lift initially increases) have been obtained, similar adverse lift effects have been measured in experiments.

Type
Inviscid theory of two-dimensional aerofoil/spoiler configurations at low speed
Information
The Aeronautical Journal , Volume 91 , Issue 910 , December 1987 , pp. 492 - 498
Copyright
Copyright © Royal Aeronautical Society 1987 

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. Leonard, A. Vortex Methods for Flow Simulation, J Comp Phys, 1980, 37, 289.Google Scholar
2. Moore, D. W. A Numerical Study of the Roll-Up of a Finite Vortex Sheet. J Fluid Mech, 1974, 63, part 2, 225–235.Google Scholar
3. Bromilow, I. G. and Clements, R. R. Some Techniques for Extending the Application of the Discrete Vortex Method of Flow Simulation. The Aeronautical Quarterly, February 1982.Google Scholar
4. Sarpkaya, T. and Schoaff, R. L. Inviscid Model of Two-Dimensional Vortex Shedding by a Circular Cylinder. AIAA Journal, November 1979, 17, 11.Google Scholar
5. Sarpkaya, T. An Inviscid Model of Two-Dimensional Vortex Shedding for Transient and Asymptotically Steady Separated Flow over an Inclined Plate. J Fluid Mech, 1975, 68. part 1. 109–128.Google Scholar
6. Clements, R. R. An Inviscid Model of Two-Dimensional Vortex Shedding. J Fluid Mech, 1973, 57, part 2, 321–336.Google Scholar
7. Clements, R. R. and Maull, D. J. The Representation of Sheet of Vorticity by Discrete Vortices. Prog Aerospace Sci, 1975, 16, No 2, 129–146.Google Scholar
8. Lee, C. S. and Bodapati, S. Comparison between Theoretical and Experimental Flow Fields of an Airfoil with Deflected Spoiler. AIAA, -85-0269.Google Scholar
9. Mabey, D. G. A Review of Some Recent Research on Time-Dependent Aerodynamics. The Aeronautical Journal, February 1984.Google Scholar
10. Consigney, H., Gravelle, A. and Molinaro, R. Aerodynamic Characteristics of a Two-Dimensional Moving Spoiler in Subsonic and Transonic Flow. J Aircraft, September 1984, 21, No 9.Google Scholar
11. Brown, G. P. and Parkinson, G. V. A Linearised Potential Flow Theory for Airfoils with Spoilers. J Fluid Mech, 1973, 57, part 4. 695–719.Google Scholar
12. Hancock, G. J. The Overall Forces on Systems of Discrete Vortices. QMC EP Report 1072, 1985.Google Scholar