Research Article

Computational Investigations on the Effects of Gurney Flap on Airfoil Aerodynamics

Table 1

Comparison of values at AoA = 12° for different GF heights.

Computational % increaseExperimental % increase

0.01.1281.165
0.51.38222.61.29911.5
1.01.4978.31.44611.3
1.51.5956.61.5285.6
2.01.6674.51.5803.5
3.01.7826.91.6464.1
4.01.8775.4