All tests were conducted at a Reynolds number of 2.2 and a Mach number of 0.13.
Wind tunnel force and pressure tests were conducted for the GA(W)- 1 airfoil equipped with a 20% aileron, and pressure tests were conducted with a 30% Fowler flap. A series of comparative tests of vortex generators applied to the ( GA-W)- 1 airfoil show that triangular planform vortex generators are superior to square planform vortex generators of the same span.įorce and pressure tests of the GA(W)- 1 airfoil with a 20% aileron and pressure tests with a 30% Fowler flap Spoiler cross-sectional shape variations generally have a modest influence on control characteristics. It is found that providing a vent path allowing lower surface air to escape to the upper surface as the spoiler opens alleviates control reversal and hysteresis tendencies. Tests of several spoiler configurations show adequate control effectiveness with flap nested. Two-dimensional wind-tunnel tests were conducted to determine effectiveness of spoilers applied to the GA(W)- 1 airfoil.
Effectiveness of spoilers on the GA(W)- 1 airfoil with a high performance Fowler flap
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