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A Concise Theoretical Method for Profile-Drag Calculation; Advance ReportIn this report a method is presented for the calculation of the profile drag of airfoil sections. The method requlres only a knowledge of the theoretical velocity distribution and can be applied readily once this dlstribution is ascertained. Comparison of calculated and experimental drag characteristics for several airfoils shows a satisfactory agreement. Sample calculatlons are included.
Document ID
20110020378
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Nitzberg, Gerald E. (National Advisory Committee for Aeronautics. Ames Aeronautical Lab. Moffett Field, CA, United States)
Date Acquired
September 7, 2013
Publication Date
February 1, 1944
Subject Category
Aerodynamics
Report/Patent Number
NACA ACR No. 4B05
Report Number: NACA ACR No. 4B05
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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