International Journal of Rotating Machinery / 2015 / Article / Tab 4

Research Article

Effect of Reynolds Number on Aerodynamics of Airfoil with Gurney Flap

Table 4

Percentage Increment 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 GF1.272.523.595.7110.30
 With GF0.731.512.183.456.40
 Without GF1.302.583.665.7810.26
 With GF0.831.622.313.566.25
12°
 Without GF1.392.653.695.8110.07
 With GF1.031.912.623.946.60