Summary
According to a criterion proposed by Poll, leading edge contamination by a turbulent boundary layer occurs when a characteristic Reynolds number \(\bar{R}\) * exceeds a critical threshold. Two series of experiments have been performed in order to assess the validity of this criterion. The first one was carried out on a swept cylinder at Mach 3. In the second series of experiments, a swept wing was designed with a leading edge providing values of \(\bar{R}\) * close to the flight values of the inner wing of a supersonic transport aircraft at Mach 2. Both experiments indicated that the leading edge flow became turbulent for values of \(\bar{R}\) * in rough agreement with Poll’s criterion. Additional experiments were performed in order to investigate the effects of roughness elements placed on and off the attachment line.
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References
D. Arnal and J.C. Juillen. Etude de la transition et de la contamination de bord d’attaque sur ailes en flèche. AGARD CP 438, 1988.
D. Arnal, F. Vignau, and F. Laburthe. Recent supersonic transition studies with emphasis on the swept cylinder case. Conf. on Boundary Layer Transition and Control, Cambridge, April 1991.
D.M. Bushnell and J.K. Huffman. Investigation of heat transfer to leading edge of a 76° swept fin with and without chordwise slots and correlations of swept-leadingedge transition data for Mach 2 to 8. Technical Report TM-X-1475, NASA, 1967.
J.L. Da Costa. Contribution à l’étude de la transition de bord d’attaque par contamination en écoulement hypersonique. Master’s thesis, Poitiers University, France, 1990.
T.R. Creel. Effects of sweep angle and passive relaminarisation devices on a supersonic swept-cylinder boundary layer. AIAA 91–0066, January 1991.
L. Gaillard. Etude de la transition de bord d’attaque sur un cylindre en flèche en écoulement hypersonique. Master’s thesis, Poitiers University, France, 1993.
M. Gaster. On the flow along leading edges. The Aeron. Quarterly, XVIII, Part2, May 1967.
E.L. Morrisette. Roughness induced transition criteria for space shuttle-type vehicles. J. of Aircraft, 13 (2), February 1976.
W. Pfenninger. Flow phenomena at the leading edge of swept wings. AGARDograph 97, Part 4, 1965.
D.I.A. Poll. Some aspects of the flow near a swept attachment line with particular reference to boundary layer transition. Technical Report 7805./K, Cranfield, College of Aeronautics, August 1978.
D.I.A. Poll. Boundary layer transition on the windward face of space shuttle during reentry. AIAA Paper 85–0899, 1985.
J. Reneaux, J. Preist, J.C. Juillen, and D. Arnal. Control of attachment line contamination. 2nd European Forum on Laminar Flow Technology, Bordeaux, June 1996.
A.S. Skuratov and A.V. Fedorov. The laminar-turbulent transition past roughness at the attachment line of a swept cylinder in supersonic flow. Izv. AN SSSR, Mekh. Zhidk. i Gasa (translated in english), (6): 28–35, 1991.
A.M. Vuillot, V. Couaillier, and N. Liamis. Turbomachinery Euler and Navier-Stokes calculations with a multidomain cell-centered approach. AIAA Paper 93–2576, 1993.
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Arnal, D., Reneaux, J. (2001). Attachment Line Transition in Supersonic Flow. In: Thiede, P. (eds) Aerodynamic Drag Reduction Technologies. Notes on Numerical Fluid Mechanics (NNFM), vol 76. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-540-45359-8_15
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DOI: https://doi.org/10.1007/978-3-540-45359-8_15
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