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A new approach to adaptive-wall windtunnel testing

Published online by Cambridge University Press:  04 July 2016

E. Fakas  and
L. Bernstein
E. Fakas
Affiliation:
Department of Aeronautical EngineeringQueen Mary and Westfield College, University of London
L. Bernstein
Affiliation:
Department of Aeronautical EngineeringQueen Mary and Westfield College, University of London
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Summary

A technique is described whereby experiments may be conducted on models which are geometrically similar to only part of the full scale configuration with the windtunnel walls being contoured to simulate the flow over that part. In this way, higher spatial resolutions can be achieved in a windtunnel of moderate size. The method is demonstrated by studying the effects of tip geometry on the flow over a wing of aspect ratio 15 using a half wing model of chord 500 mm projecting 1031 mm into a test section of width 1200 mm.

Type
Research Article
Information
The Aeronautical Journal , Volume 98 , Issue 972 , February 1994 , pp. 60 - 68
Copyright
Copyright © Royal Aeronautical Society 1994 

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References

1. Boundary layer simulation and control in wind-tunnels, AGARD AR-224,1988.Google Scholar
2. Wall interference in windtunnels, AGARD CP-335, 1982.Google Scholar
3. Sears, W.R. Self-correcting windtunnels, Aeronaut J, 1974, 78, pp 80–89.Google Scholar
4. Sears, W.R. Interference-free windtunnel flows by adaptive-wall technology,.ICAS Paper 76-02, 1976.Google Scholar
5. Goodyer, M.J. A low-speed self-streamlining windtunnel, In: Wind-tunnel design and testing techniques, AGARD CP-174, 1975.Google Scholar
6. Goodyer, M.J. and Wolf, S.W.D. Development of a self-streamlining, flexible-walled, transonic test-section, AIAA J, 1982, 20, pp 227–234.Google Scholar
7. Newman, P.A., Anderson, E.C. and Peterson, J.B. Aerodynamic design of the contoured wind-tunnel liner for the NASA supercritical, laminar-flow-control, swept-wing experiment, NASA TP-2335, 1984.Google Scholar
8. Spivey, W.A. and Moorhouse, G.G. New insights into the design of swept-tip rotor-blades, 26th Annual National Forum of the American Helicopter Society, 1970.Google Scholar
9. Wilby, P.G. and Philippe, J.J. An investigation of the aerodynamics of an RAE swept-tip using a model rotor, VIIIth European Rotorcraft Forum, 1982.Google Scholar
10. Fakas, E. Aerodynamics of helicopter rotor blade tips, PhD thesis, University of London, 1990.Google Scholar
11. Spivey, W.A. Blade tip aerodynamics, profile and planform shapes, 24th Annual National Forum of the American Helicopter Society, 1968.Google Scholar
12. Spivey, W.A. A Study to investigate the aerodynamics of rotor-blade tip shapes, Bell Helicopter Rep. 299-099-468,1970.Google Scholar
13. Srinivasan, G.R., McCroskey, W.J., Baeder, J.D. and Edwards, T.A. Numerical simulation of tip vortices of wings in subsonic and transonic flows, AIAA J, 1988,26, pp 1153–1162.Google Scholar
14. Xenophontos, X.M. An experimental investigation into the turbulent boundary layer on a wing tip, PhD Thesis, University of London, 1984.Google Scholar