FORCE AND PRESSURE TESTS OF THE GA(W)-1 AIRFOIL WITH A 20% AILERON AND PRESSURE TESTS WITH A 30% FOWLER FLAP

摘要

Wind-tunnel force and pressure tests have been conducted for the GA(W)-1 airfoil equipped with a 20% aileron, and pressure tests have been conducted with a 30% Fowler flap. All tests were conducted at a Reynolds number of 2.2 x 106 and a Mach number of 0.13. The aileron provides control effectiveness similar to ailerons applied to more conventional airfoils. Effects of aileron gaps from 0% to 2% chord were evaluated, as well as hinge moment characteristics. The aft camber of the GA(W)-1 section results in a substantial up-aileron moment, but the hinge moments associated with aileron deflection are similar to other configurations.nFowler flap pressure distributions indicate that unseparated flow is achieved for flap settings up to 40°, over a limited angle-of-attack range. Theoretical pressure distributions compare favorable with experiment for low flap deflections, but show substantial errors at large deflections.