Experimental study of delta wing leading-edge devices for drag reduction at high lift

Author:: Rao, D. M.
Published:: Feb 1, 1982.
Physical Description:: 1 electronic document
Additional Creators:: Johnson, T. D., Jr.

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Summary:

The drag reduction devices selected for evaluation were the fence, slot, pylon-type vortex generator, and sharp leading-edge extension. These devices were tested on a 60 degree flatplate delta (with blunt leading edges) in the Langley Research Center 7- by 10-foot high-speed tunnel at low speed and to angles of attack of 28 degrees. Balance and static pressure measurements were taken. The results indicate that all the devices had significant drag reduction capability and improved longitudinal stability while a slight loss of lift and increased cruise drag occurred.

Other Subject(s):

AERODYNAMICS

Collection:

NASA Technical Reports Server (NTRS) Collection.

Note:

Document ID: 19820011291.
Accession ID: 82N19165.
NASA-CR-165846.

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