STOL aircraft obtain their unique performance by incorporating in their design any one or all of three design aspects: increase of the powerplant size to minimize the weight-tothrust ratio, increase of the wing area to reduce the wing loading, and/or increase of the maximum obtainable lift coefficient.
A special powered STOL light aircraft wing has been developed at West Virginia University. This wing combines several STOL features such as: circulation control through blowing around a circular trailing edge, boundary layer control through suction, leading edge modification and slats, 20% increase in chord length in the STOL mode, blown and drooped ailerons, and fences for maximum spanwise lift distribution.
This wing was designed at West Virginia University and is based on the results of theoretical analysis and wind tunnel tests of several other configurations. The wing has been built and is to be test flown in spring 1973 on a light aircraft called the Technology Demonstrator. The wing design features and anticipated performance are described.