Reduction of profile drag at supersonic velocities by the use of airfoil sections having a blunt trailing edge Page: 1 of 30
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NATIONAL ADVISORY COMMITTEE
FOR AERONAUTICS
TECHNICAL NOTE 3503
REDUCTION OF PROFILE DRAG AT SUPERSONIC VELOCITIES
BY THE USE OF AIRFOIL SECTIONS HAVING
A BLUNT TRAILING EDGE
By Dean R. Chapman
Ames Aeronautical Laboratory
Moffett Field, Calif.
Washington
September 1955Sifw tR If L qf'R
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Chapman, Dean R. Reduction of profile drag at supersonic velocities by the use of airfoil sections having a blunt trailing edge, report, September 1955; (https://digital.library.unt.edu/ark:/67531/metadc57509/m1/1/: accessed April 25, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.