An Analytical and Experimental Study of the Steady and Unsteady Airloads on a Wing with Oscillating Control Including a Streamlined Gap

摘要

A wing section with oscillation control was studied in a 3m low speed wind tunnel. In order to simulate a realistic configuration, the gap between wing and control surface was streamlined. A modified analytical surface singularity method, taking into account the exact boundary conditions and Bernoulli equation, was developed. With this method the problem is handled as an inteference problem between two lifting bodies with two Kutta conditions. Local lift distributions obtained from both experiment and theory are compared for a variety of parameters, such as aspect ratio, section incidence, steady flap deflection, oscillation frequency, wake location, and open/closed slot. Outside the gap the correspondence between the exact potential theory and the experimental data is excellent. Deviations within the gap region are attributed to viscous effects.