Reflection-Plane Tests of Spoilers on an Advanced Technology Wing

Tests of a finite-span wing with an advanced technology GA(W)-1 airfoil, spoilers, and 30% full-span Fowler flap have been conducted utilizing a reflection-plane model in the WSU low speed wind tunnel. Flap settings from 0° to 40° were tested with a series of 10% chord spoilers of various cross-sectional shapes. Wing force and spoiler hinge moment measurements were made, as well as tuft studies of stalling patterns.

Results show that a finite span (aspect ratio 9.5) C_Lmax value of 3.0 can be obtained with 40° flap at a Reynolds number of 1.0 x 10⁶. Spoiler results correlate well with two-dimensional results, which show that satisfactory roll control can be obtained for all flap settings, with proper lower surface venting. Spoiler gap leak lift and drag penalties were found to be quite substantial, indicating a need for careful design of gaps and seals for flap and spoiler nested configurations.