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Numerical study of active shock control for transonic aerodynamics

N. Qin (Department of Mechanical Engineering, University of Sheffield, Sheffield, UK)
Y. Zhu (Department of Mechanical Engineering, Brunel University, Uxbridge, UK)
S.T. Shaw (College of Aeronautics, Cranfield University, Bedford, UK)

International Journal of Numerical Methods for Heat & Fluid Flow

ISSN: 0961-5539

Article publication date: 1 June 2004



In this paper, the effectiveness of a number of active devices for the control of shock waves on transonic aerofoils is investigated using numerical solutions of the Reynolds‐averaged Navier‐Stokes equations. A brief description of the flow model and the numerical method is presented including, in particular, the boundary condition modelling and the numerical treatment for surface mass transfer. Comparisons with experimental data have been made where possible to validate the numerical study before some systematic numerical simulations for a parametric study. The effects of surface suction, blowing, and local modification of the surface contour (bump) on aerofoil aerodynamic performance have been studied extensively regarding the control location, the mass flow strength and the bump height. The numerical simulations highlight the benefits and drawbacks of the various control devices for transonic aerodynamic performance and identify the key design parameters for optimisation.



Qin, N., Zhu, Y. and Shaw, S.T. (2004), "Numerical study of active shock control for transonic aerodynamics", International Journal of Numerical Methods for Heat & Fluid Flow, Vol. 14 No. 4, pp. 444-466.



Emerald Group Publishing Limited

Copyright © 2004, Emerald Group Publishing Limited

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