抄録
This paper describes an experimental investigation on a state-ofthe-
art compressor airfoil with three different leading edges at high
subsonic flow conditions. In addition to a conventional circular and
elliptical geometry which possess curvature discontinuities at the
blend points, a continuous curvature leading edge is studied. The
investigation considers the performance at design incidence, as well
as the impact of off-design incidences.
Pressure spikes near the leading edge can lead to early transition
associated with higher profile losses. Goodhand and Miller [1]
showed that in low subsonic conditions the avoidance of curvature
discontinuities can diminish pressure spikes and therefore reduce
the profile losses and enlarge the working range. In this paper,
measurements are conducted to assess the potential of this concept
for a high-pressure jet engine compressor airfoil operated at high
subsonic conditions (M1 = 0:7, Red=2 = 20;000). The results show
that, at design incidence, the total pressure loss coefficient of the
continuous curvature leading edge reduces by up to 15:4%compared
to the circular leading edge and by up to 3:1 % for the elliptical
geometry. At off-design incidence, the reduction can be up to 40:2 %
at maximum positive incidence under consideration.
