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 | % increase | Experimental | % increase |
| 0.0 | 1.128 | — | 1.165 | — | 0.5 | 1.382 | 22.6 | 1.299 | 11.5 | 1.0 | 1.497 | 8.3 | 1.446 | 11.3 | 1.5 | 1.595 | 6.6 | 1.528 | 5.6 | 2.0 | 1.667 | 4.5 | 1.580 | 3.5 | 3.0 | 1.782 | 6.9 | 1.646 | 4.1 | 4.0 | 1.877 | 5.4 | — | — |
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