Reynolds Number Influence on 2-D Compressible Dynamic Stall
Abstract
Reynolds number effects on oscillating airfoil
compressible dynamic stall flow have been investigated.
The Reynolds number was doubled at constant
Mach number by using two (untripped and
tripped) NACA 0012 airfoils, one with 3-inch chord
and another with 6-inch chord. Pressure distributions
documented using point diffraction interferometry(
PDI) are compared with each other for Mach
numbers of 0.3 and 0.45 at different reduced frequencies.
Comparisons with a reference data set at
Re = 4 x 106 for a Mach number of 0.3 at reduced
frequencies of 0.05 and 0.1 showed good agreement
for the tripped 6-inch airfoil, thus establishing a minimum
model Reynolds number for simulating full-scale
results. Reynolds number influence manifests as an
increase in the airfoil peak suction pressure coefficient,
smaller laminar separation bubble, increase in
dynamic stall onset angle, and an increased ability to
withstand adverse pressure gradient in the flow. At
lower Reynolds numbers, dynamic stall arises from
the bursting of the laminar separation bubble at both
M = 0.3 and 0.45. At higher effective Reynolds numbers,
dynamic stall is induced by large adverse pressure
gradient in the flow for M = 0.3 and shock induced
dynamic stall onset for at M = 0.45.
Description
AIAA Paper 96-0073 , Reno, NV, Jan. 1996.
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