Wk. Anderson et al., NAVIER-STOKES COMPUTATIONS AND EXPERIMENTAL COMPARISONS FOR MULTIELEMENT AIRFOIL CONFIGURATIONS, Journal of aircraft, 32(6), 1995, pp. 1246-1253
A two-dimensional unstructured Navier-Stokes code is utilized for comp
uting the flow around multielement airfoil configurations. Comparisons
are shown for a landing configuration with an advanced-technology fla
p. Grid convergence studies are conducted to assess inaccuracies cause
d by inadequate grid resolution, Although adequate resolution is obtai
ned for determining the pressure distributions, further refinement is
needed to sufficiently resolve the velocity profiles at high angles of
attack. For the advanced flap configuration, comparisons of pressure
distributions and lift are made with experimental data. Here, two flap
riggings and two Reynolds numbers are considered. In general, the tre
nds caused by variations in these quantities are well predicted by the
computations, although the angle of attack for maximum lift is overpr
edicted.