Hot-wire measurements have been made in the boundary
layer, the separated region, and the near wake for flow
past an NACA 4412 airfoil at maximum lift. The
Reynolds number based on chord was about 1,500,000.
Special care was taken to achieve a two-dimensional
mean flow. The main instrumentation was a hot-wire
probe mounted on the end of a rotating arm. An unexpected
effect of rotor interference was identified and
brought under control. A digital computer was used to
control synchronized sampling at closely spaced points
along the probe arc. Ensembles of data were obtained
at several thousand locations in the flow field. The
data include intermittency, two components of mean
velocity, and twelve mean values for double, triple,
and quadruple products of two velocity fluctuations.
The data are available on punched cards in raw form
and also after use of smoothing and interpolation routines
to obtain values on a fine rectangular grid aligned with
the airfoil chord
