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A nonlinear theory for airfoils with trailing-edge jet flapA nonlinear procedure for computing the pressure distribution on an airfoil with a trailing edge jet flap is described. The method is not restricted to thin airfoils or shallow jet-deflection angles. Correlation with experiment indicates that the characteristics of the pressure distribution are predicted by the theory, but the effect of entrainment is overpredicted with the entrainment coefficient used.
Document ID
19770009038
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Technical Note (TN)
Authors
Barger, R. L. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 3, 2013
Publication Date
December 1, 1976
Subject Category
Aerodynamics
Report/Patent Number
NASA-TN-D-8368
L-11126
Report Number: NASA-TN-D-8368
Report Number: L-11126
Accession Number
77N15981
Funding Number(s)
PROJECT: RTOP 505-06-31-02
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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