Wind-tunnel Investigation of Effects of Rear Upper Surface Modification on a NASA Supercritical Airfoil

Author:: Blackwell, J. A., Jr.
Published:: Jan 1, 1972.
Physical Description:: 1 electronic document
Additional Creators:: Harris, C. D.

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Summary:

Wind tunnel tests were conducted at Mach numbers from 0.60 to 0.81 to examine the effects on supercritical airfoil of modifying the rear upper surface to reduce the magnitude of an intermediate off design second velocity peak. The modification was accomplished by increasing the upper surface curvature around the 50 percent chord station and reducing the curvature over approximately the rearmost 30 percent of the airfoil while maintaining the same trailing edge thickness.

Other Subject(s):

AERONAUTICS (GENERAL)

Collection:

NASA Technical Reports Server (NTRS) Collection.

Note:

Document ID: 19830002750.
Accession ID: 83N11020.
NASA-TM-X-2454.
NAS 1.15:X-2454.
L-7983.

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