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Implications of compressibility effects for Reynolds-scaled testing of an inverted wing in ground effect
International Journal of Aerodynamics
  • G. Doig, University of New South Wales
  • Tracie J. Barber, University of New South Wales
  • Sammy Diasinos, Macquarie University
Publication Date
1-1-2014
Abstract

The influence of compressibility around an isolated inverted wing at a fixed Reynolds number was examined as relevant to the issue of wind tunnel scaling effects. Three-dimensional simulations were conducted for low ground clearances, at: full scale and a Mach number of 0.088, at 50% scale at Mach 0.176, and at 25% scale at Mach 0.352. As the scale was reduced, the increasing peak local Mach number between the wing and the ground resulted in a higher propensity of the flow to separate towards the trailing edge, and for incompressible or full-scale CFD to underestimate the lift and drag coefficients by an ever-increasing margin. The lower vortex path was less affected. The results suggest that compressible CFD of a scale experiment ought to be conducted at the same Reynolds number and Mach number as the tunnel test for the best possible correlation at free-stream Mach numbers beyond 0.15.

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Citation Information
G. Doig, Tracie J. Barber and Sammy Diasinos. "Implications of compressibility effects for Reynolds-scaled testing of an inverted wing in ground effect" International Journal of Aerodynamics Vol. 4 Iss. 3/4 (2014) p. 135 - 153
Available at: http://works.bepress.com/gcdoig/6/