22nd Congress of International Council of the Aeronautical Sciences, Harrogate, UK, 28 August - 1st September, 2000
Paper ICAS 2000-2.9.R2
EXPERIMENTAL INVESTIGATION OF FLOWFIELD OVER A MULTI-ELEMENT AEROFOIL AND COMPARISON WITH COMPUTATIONAL PREDICTION
H. H. BRUUN, S. R. MADDAH
University of Bradford, UK
Keywords: multi-element aerofoil, fhw, rsm
This paper presents results obtained from a
combined experimental and computational
study of the flowfield over a multi-element
aerofoil with and without an advanced slat.
Detailed measurement of the mean flow and
turbulent quantities over a multi-element
aerofoil model in a wind tunnel have been made
using pressure, stationary and flying hot-wire
(FHW) probes. The model configuration spans
the test section and is made of three parts: 1) an
advanced slat, 2) a NACA 4412 main aerofoil,
3) a NACA 4415 flap. The chord lengths of the
elements were 38, 250 and 83 mm respectively.
The results were obtained at a chord Reynolds
number of 2.5×105 and a free Mach number of
less than 0.1. The slat performance at different
angles of attack, a, were investigated and
compared with cases without the slat.
Numerical predictions have been obtained by
solving the time-averaged Navier-Stokes
equations incorporating a Reynolds Stress
Model (RSM) for the same configurations. This
paper presents results for both experimental
and numerical selected cases placing the multielement
aerofoil at angles of attack of 15° and
20° with the advanced slat and 5° and 15°
without employing the advanced slat. The
computational results are compared with
experimental data, which showed excellent
agreement for low angle of attack and good
agreement for other cases without separation,
taking into account errors in both the
experimental and numerical results. However,
discrepancies were in particular observed in the
complicated shear layers and high turbulent
intensity regions due to limitations in the
turbulence model and also inadequate grid
resolution.
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