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Estimation of attainable leading-edge thrust for wings at subsonic and supersonic speedsThe factors which place limits on the theoretical leading edge thrust are identified. An empirical method for the estimation of attainable thrust is presented. The method is based on the use of simple sweep theory to permit a two dimensional analysis, the use of theoretical airfoil programs to define thrust dependence on local geometric characteristics, and the examination of experimental two dimensional airfoil data to define limitations imposed by local Mach numbers and Reynolds numbers. Comparisons of theoretical and experimental aerodynamic characteristics for a series of wing body configurations are examined.
Document ID
19800001866
Document Type
Technical Publication (TP)
Authors
Carlson, H. W. (NASA Langley Research Center Hampton, VA, United States)
Mack, R. J. (NASA Langley Research Center Hampton, VA, United States)
Barger, R. L. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
January 1, 1979
Subject Category
AERODYNAMICS
Report/Patent Number
L-13032
NASA-TP-1500
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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