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An investigation was performed to evaluate a novel and inexpensive wind tunnel model mount for dynamic aerodynamic testing. A computer analysis code was developed to identify the dimensions of the control surface needed to produce a desired pitching motion for a delta wing. The code was then used to design and build a dynamic model apparatus that was evaluated in a low speed wind tunnel at Wichita State University. The dynamic model mount and control were evaluated for a variety of motions, including constant pitch rate ramps, constant frequency oscillations and impulse or step inputs. Results from the ramp and oscillation test indicated the system is very responsive and capable of a wide range of motion.

A high lift, low Reynolds number airfoil section has been designed, built, and tested for a Short Take-Off and Landing (STOL) aircraft configuration. The wing incorporating this airfoil section was augmented with a full span non-adjustable external flap, and a partial span adjustable spoiler. Optimum configuration for the flap and spoiler were determined experimentally at Wichita State University's low speed wind tunnel. Flight test of this configuration indicated excellent lift carrying capability.