An evaluation was conducted to document the two-dimensional power augmented wing in ground effect phenomena. 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. (Author)
An Evaluation of a Two-Dimensional Power Augmented Wing in Ground Effect Model under Static and Dynamic Freestream Conditions
1976
44 pages
Report
Keine Angabe
Englisch
Aircraft , Aerodynamics , Ground effect machines , Wings , Wind tunnel tests , Two dimensional , Powered lift , Augmentation , Static tests , Dynamic tests , Thrusters , Compressed air , Plane geometry , Lift , Lift to drag ratio , Angle of attack , Trailing edges , Coefficients , Pressure distribution , Thrust augmentation , Flaps(Control Surfaces) , Test and evaluation , Free stream , NACA 66-210 Airfoils
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