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Wind-tunnel results for a modified 17-percent-thick low-speed airfoil section

Author
Beasley, W. D.
Published
Nov 1, 1981.
Physical Description
1 electronic document
Additional Creators
Mcghee, R. J.
Online Version

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Restrictions on Access
Unclassified, Unlimited, Publicly available.
Free-to-read Unrestricted online access
Summary
Wind-tunnel tests were conducted in the Langley low-turbulence pressure tunnel to evaluate the effects on performance of modifying a 17-percent-thick low-speed airfoil. The airfoil contour was altered to reduce the pitching-moment coefficient by increasing the forward loading and to increase the climb lift-drag ratio by decreasing the aft upper surface pressure gradient. The tests were conducted over a Mach number range from 0.07 to 0.32, a chord Reynolds number range 1.0 x 10 to the 6th power to 12.0 x 10 to the 6th power, and an angle-of-attack range from about -10 deg to 20 deg.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19820003160.
Accession ID: 82N11033.
L-14666.
NASA-TP-1919.
Terms of Use and Reproduction
No Copyright.
View MARC record | catkey: 15717767