Research Article
Computational Investigations on the Effects of Gurney Flap on Airfoil Aerodynamics
Table 3
Comparison of
values for different mounting angles of 1.5% GF at AoA =12
°.
| | (Deg.) | Computational | % decrease in with respect to | Experimental | % decrease in with respect to |
| | 120 | 1.554 | 2.61 | — | — | | 105 | 1.568 | 1.73 | — | — | | 90 | 1.595 | — | 1.611 | — | | 75 | 1.592 | 0.23 | — | — | | 60 | 1.573 | 1.39 | 1.580 | 1.87 | | 45 | 1.541 | 3.39 | 1.544 | 4.10 | | 30 | 1.467 | 8.00 | — | — |
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