International Journal of Rotating Machinery / 2015 / Article / Tab 3

Research Article

Effect of Reynolds Number on Aerodynamics of Airfoil with Gurney Flap

Table 3

Percentage Decrement in per every 10,000 decrease in Reynolds number for different ranges of Reynolds number.

Reynolds number range
AoA,
to

to

to

to

to

 Without GF0.120.250.370.571.12
 With GF0.180.490.861.573.41
 Without GF0.150.310.450.721.30
 With GF0.200.500.821.402.74
12°
 Without GF0.250.500.660.981.62
 With GF0.420.851.171.652.51