Hostname: page-component-848d4c4894-2xdlg Total loading time: 0 Render date: 2024-06-26T02:37:47.404Z Has data issue: false hasContentIssue false
  • English
  • Français

Pneumatic flow control studies using steady blowing on a supercritical aerofoil

Published online by Cambridge University Press:  03 February 2016

C. Wong  and
K. Kontis
C. Wong
Affiliation:
Aero-Physics Laboratory, School of Mechanical, Aerospace and Civil Engineering, University of Manchester, Manchester, UK
K. Kontis
Affiliation:
Aero-Physics Laboratory, School of Mechanical, Aerospace and Civil Engineering, University of Manchester, Manchester, UK
Get access Rights & Permissions [Opens in a new window]

Abstract

Experimental studies have been conducted on a NASA 17-percent thick supercritical aerofoil with a Coanda trailing edge at subsonic speeds in both the boundary-layer control and circulation control regimes. Detailed boundary-layer surveys were performed along the mid span on the suction surface and around the Coanda trailing edge. The wake located at 43% chord-length behind the aerofoil was measured with a single-component hotwire anemometer, and the profile drag coefficients were calculated from the integration of wake momentum deficit. Lift forces and pitching moments were recorded from –20deg to +20deg incidence using a 3-component force balance. In the circulation control regime, the boundary-layer results indicated that separation bubbles are not present at high incidences compared to the boundary-layer control regime, and that minimised the potential for flow separation delay around the Coanda trailing edge. The spectral analysis of the wake showed a significant reduction of wake fluctuations at high incidences and improvement of the stability at the edge of the wake. The study of aerodynamic forces suggested the need to increase the blowing momentum coefficient if the circulation control is used near the stalling angle-of-attack.

Type
Research Article
Information
The Aeronautical Journal , Volume 113 , Issue 1139 , January 2009 , pp. 53 - 63
Copyright
Copyright © Royal Aeronautical Society 2009 

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. Jones, G.S., Pneumatic flap performance for a two-dimensional circulation control airfoil, Applications of Circulation Control Technology, Joslin, R.D. and Jones, G.S., (Eds), 214, AIAA, Virginia, USA, 2006, pp 191–243.Google Scholar
2. Karamcheti, K., Principles of Ideal Fluid Aerodynamics, John Wiley and Sons, 1996, pp 376–401.Google Scholar
3. Metral, A.R., On the phenomenon of fluid veins and their applications, the Coanda effect, AF Translation, F-TS-786-RE, 1939.Google Scholar
4. Kind, R.J. and Maull, D.J., An experimental investigation of a low-speed circulation-controlled aerofoil, The Aeronaut Q, 1967, 19, pp 170–182.Google Scholar
5. Englar, R.J., Circulation control pneumatic aerodynamics: blown force and moment augmentation and modifications; past, present and future, AIAA Paper 00-2541, 2000.Google Scholar
6. Lin, Y., Sarkar, L.N., Englar, R.J. and Ahuja, K.K., Numerical simulations of steady and unsteady aerodynamics characteristics of a circulation vontrol aerofoil, AIAA Paper 01-0704, 2001.Google Scholar
7. Wood, N. and Nielson, J., Circulation control airfoils past, present, and future, AIAA Paper 85-0204, 1985.Google Scholar
8. Englar, R.J., Low-speed aerodynamics characteristics of a small fixed trailing-edge circulation control wing configuration fitted to a supercritical airfoil, David, W., Taylor Naval Ship Research and Development Center Bethesda Maryland 20084, USA, March 1981.Google Scholar
9. Loth, J.L. and Boasson, M., Circulation controlled STOL wing optimisation, J Aircr, 1983, 21, (2), pp 128–134.Google Scholar
10. Imber, R. and Rogers, E., Investigation of a circular planform wing with tangential fluid ejection, AIAA Paper 96-0558, 1996.Google Scholar
11. Loth, J.L., Fanucci, J.B. and Roberts, S.C., Flight performance of a circulation controlled STOL aircraft, J Aircr, 1976, 13, (3), pp 169–173.Google Scholar
12. Spaid, F.W. and Keener, E.R., Boundary-Layer and wake measurements on a swept, circulation-control Wing, J Aircr, 1991, 28, (11), pp 706–712.Google Scholar
13. Jones, G.S., Viken, S.A., Washburn, A.E., Jenkins, L.N. and Cagle, G.M., An active flow circulation controlled flap concept for general aviation aircraft applications, AIAA Paper 02-3157, 2002.Google Scholar
14. Poisson-Quinton, P. and Lepage, L., Survey of French Research on the Control of Boundary Layer and Circulation, Boundary Layer and Flow Control, Lachmann, G. (Ed), 1, Pergamon Press, New York, USA, pp 21–73.Google Scholar
15. Jones, G.S., Pneumatic Flap Performance for a 2D Circulation Control Airfoil, Steady & Pulsed, NASA LaRC Rept. 2005.Google Scholar
16. Wilson, M.B. and Kerczek, C.V., An Inventory of Some Force Producers for use in Marine Vehicle Control, DTNSRDC-79/097, 1979.Google Scholar
17. Harris, C.D., NASA Supercritical Aerofoils, A Matrix of Family related Airfoils, NASA Technical Paper 2969, March 1990·Google Scholar
18. McGbee, R.J. and Beasley, W.D., Low-speed aerodynamic characteristics of a 17-percent-thick airfoil section designed for general aviation applications, NASA Technical Note D-7428, 1973.Google Scholar
19. Wong, C.W., Flow Control Effectiveness of Pneumatic Actuators with Generic Bodies at Subsonic Speeds, The University of Manchester, PhD Thesis, Manchester, UK, March 2007.Google Scholar
20. Bruun, H.H., Hot-Wire Anemometry, Oxford University Press, Oxford, UK, 1995, pp 33–34.Google Scholar
21. Jones, B.M., Measurement of profile drag by the pitot traverse method, British ARC R&M 1688, 1936.Google Scholar