Hostname: page-component-77c89778f8-cnmwb Total loading time: 0 Render date: 2024-07-22T10:20:39.957Z Has data issue: false hasContentIssue false
  • English
  • Français

Effects of leading-edge bevel angle on the aerodynamic forces of a non-slender 50° delta wing

Published online by Cambridge University Press:  03 February 2016

J. J. Wang  and
S. F. Lu
J. J. Wang
Affiliation:
Fluid Mechanics Institute, Beijing University of Aeronautics and Astronautics, Beijing, China
S. F. Lu
Affiliation:
Fluid Mechanics Institute, Beijing University of Aeronautics and Astronautics, Beijing, China
Get access Rights & Permissions [Opens in a new window]

Abstract

The aerodynamic performances of a non-slender 50° delta wing with various leading-edge bevels were measured in a low speed wind tunnel. It is found that the delta wing with leading-edge bevelled leeward can improve the maximum lift coefficient and maximum lift to drag ratio, and the stall angle of the wing is also delayed. In comparison with the blunt leading-edge wing, the increment of maximum lift to drag ratio is 200%, 98% and 100% for the wings with relative thickness t/c = 2%, t/c = 6.7% and t/c = 10%, respectively.

Type
Research Article
Information
The Aeronautical Journal , Volume 109 , Issue 1098 , August 2005 , pp. 403 - 407
Copyright
Copyright © Royal Aeronautical Society 2005 

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. Werle, H.. Quelques resultants experimentaux sur les ailes en fleches, aux Faibles vitesses, obtenus en tunnel hydrodynamique, La Recherché Aeronautique, 1954, 41.Google Scholar
2. Ashley, H., Katz, J., Jarrah, M.A. and Vaneck, T.. Survey of research on unsteady aerodynamic loading of delta wings, J Fluid and Structures, 1991, 5, pp 363–390.Google Scholar
3. Rockwell, D.. Three-dimensional flow structure on delta wings at high angle-of-attack: experimental concepts and issues, 1993, AIAA Paper 93-0550.Google Scholar
4. Gursul, I.. Review of unsteady vortex flows over delta wings, 2003, AIAA Paper 2003-3942.Google Scholar
5. Earnshaw, P.B.. Measurements of vortex-breakdown position at low speed on a series of sharp-edged symmetrical models, November 1964, ARC CP 828.Google Scholar
6. Bartlett, G.E. and Vidal, R.J.. Experimental investigation of influence of edge sharp on the aerodynamic characteristics of low aspect ratio wings at low speed, J Aero Sci, 1955, 22, (8).Google Scholar
7. Kegelman, J. and Roos, F.. Effects of leading-edge shape and vortex burst on the flowfield of a 70 deg sweep delta wing, January 1989, AIAA Paper, pp 1989–0086.Google Scholar
8. Pelletier, A. and Nelson, R.C.. An experimental study of static and dynamic vortex breakdown on slender delta wing planforms, 1994, AIAA Paper 94-1879-CP.Google Scholar
9. Polhamus, E.C.. Predictions of vortex lift characteristics by leading-edge suction analogy, J Aircr, 1971, 8, pp 193–199.Google Scholar
10. Ericsson, L.E. and King, H.H.C.. Effect of leading-edge cross-sectional geometry on slender wing unsteady aerodynamics, January 1992, AIAA Paper, pp 1992–0173.Google Scholar
11. Huang, X.Z., Sun, Y.Z. and Hanff, E.S.. Further investigations of leading-edge vortex breakdown over delta wings, AIAA Paper, 1997, pp 1997–2263.Google Scholar
12. Wang, J.J. and Zhan, J.X.. A new pair of leading-edge vortex structure for flow over delta wing, J of Aircr, 2005, 2005, 42, (3), pp 718–721.Google Scholar
13. Miau, J.J., Kuo, K.T., Liu, W.H., Hsieh, S.J., Chou, J.H. and Lin, C.K.. Flow developments above a 50-deg sweep delta wings with different leading-edge profiles, J of Aircr, 1995, 32, (4), pp 787–794.Google Scholar
14. Lu, S.F.. Experimental Investigations on Vortex Structures and Aerodynamics for Flow over 50 deg Sweep Delta Wings, Master thesis, Beijing University of Aeronautics and Astronautics, 2005.Google Scholar
15. Kawazoe, H., Nakamura, Y., Ono, T. and Umhimaru, Y.. Static and total pressure distributions around a thick delta wing with rounded leading-edge, 1994, AIAA Paper, pp 1994–2321.Google Scholar