An Evaluation of a Two-Dimensional Power Augmented Wing in Ground Effect Model under Static and Dynamic Freestream Conditions

An evaluation was conducted to document the two-dimensional power augmented wing in ground effect phenomenon. Tests were conducted with a NACA 66- 210 section wing and image with a two-dimensional thrustor exhausting compressed air aligned along the image plane. Results showed that power augmentation increased the lift of a wing in ground effect. The wing lift was observed to increase with increasing jet thrust. Also, the wing lift increased with increasing angle of attack and decreasing trailing edge gap. Lift coefficients as high as 2.40 were observed with a thrust coefficient of 0.48 at a trailing edge gap of 0.025c. Static augmentation ratios approaching 2.0 were observed with the same gap. The augmentation ratio increased linearly with the inverse of the thrust coefficient. The observed thrust recovery was very sensitive to the wing geometry. The largest thrust recovery was observed in the low thrust - low lift cases.