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Characteristics at Mach Number of 2.03 of a Series of Wings Having Various Spanwise Distributions of Thickness Ratio and ChordA series of semispan wing models having various spanwise distributions of both thickness ratio and chord but having the same effective thickness ratio was tested in the Langley 4-by 4-foot supersonic pressure tunnel at Mach number 2.03 and Reynolds numbers from 1.9 x 10(exp 6) to 6.5 x 10(exp 6) complex wing forms with thickened roots, extended root chords, and higher volumes show appreciably lower zero-lift wave drag coefficients than the plain swept wings. A calculative technique for the determination of wave drag has been applied to one of the complex wings of the series and good agreement is shown with experimental results. The complex wing forms showed higher drags due to lift than the plain swept wings.
Document ID
20040005869
Acquisition Source
Langley Research Center
Document Type
Other - NASA Technical Note (TN)
Authors
Robins, A. Warner
(NASA Langley Research Center Hampton, VA, United States)
Harris, Roy V., Jr.
(NASA Langley Research Center Hampton, VA, United States)
Jackson, Charlie M., Jr.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 21, 2013
Publication Date
October 1, 1960
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
NASA-TN-D-631
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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