22nd Congress of International Council of the Aeronautical Sciences, Harrogate, UK, 28 August - 1st September, 2000
Paper ICAS 2000-3.5.2

COMPUTATION OF A DYNAMICALLY DEPLOYED FLAP EMPLOYING ADAPTIVE BODY RECOVERY

J. J. Roper, J. A. Edwards
DERA Fort Halstead, Sevenoaks, UK

Keywords: dynamic, adaptive, unsteady, computation

This paper examines the effectiveness of the adaptive body recovery technique[3][4] for computing separated hypersonic flows. The Baldwin-Lomax algebraic turbulence model was added to the code and modified, through under-relaxation of the turbulent viscosity to effect transition from laminar to turbulent flows over various distances, in order to match experimental data for a series of transitional separated flows. This turbulence model was then employed, in conjunction with the moving body boundary conditions, to predict the lag in separation growth with flap angle for a rapidly deployed flap. Agreement between the computational and experimental dynamic angular lag was found to be good.

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