Wing download reduction using vortex trapping platesA download reduction technique using spanwise plates on the upper and lower wing surfaces has been examined. Experimental and analytical techniques were used to determine the download reduction obtained using this technique. Simple two-dimensional wind tunnel testing confirmed the validity of the technique for reducing two-dimensional airfoil drag. Computations using a two-dimensional Navier-Stokes analysis provided insight into the mechanism causing the drag reduction. Finally, the download reduction technique was tested using a rotor and wing to determine the benefits for a semispan configuration representative of a tilt rotor aircraft.
Document ID
19950028589
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Light, Jeffrey S. (NASA Ames Research Center Moffett Field, CA, United States)
Stremel, Paul M. (NASA Ames Research Center Moffett Field, CA, United States)
Bilanin, Alan J. (Continuum dynamics, Inc. Princeton, NJ, United States)