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Design and development of a facility for compressible dynamic stall studies of a rapidly pitching airfoilA facility for the study of dynamic stall of an airfoil undergoing a transient ramp-type pitching motion is described. The facility can produce pitch rates of 3600 deg/sec to an angle of attack of 60 deg by using a specially designed hydraulic drive with feedback control. The ramp motion generator can also generate arbitrary motion of the airfoil and thus can simulate an arbitrary aircraft maneuver. A unique airfoil support system allows unobstructed flow visualization including the complete airfoil contour, thus permitting the use of nonintrusive optical diagnostic methods for flow measurement close to the surface as well as simultaneous far-field measurements. Schlieren pictures obtained during the study reveal the instantaneous density gradients associated with dynamic stall, even under conditions of very low Mach numbers.
Document ID
19900041200
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Chandrasekhara, M. S.
(U.S. Navy-NASA Joint Institute of Aeronautics Monterey, CA, United States)
Carr, L. W.
(NASA Ames Research Center; U.S. Army, Aeroflightdynamics Directorate, Moffett Field CA, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1989
Subject Category
Research And Support Facilities (Air)
Accession Number
90A28255
Funding Number(s)
CONTRACT_GRANT: AF-AFOSR-88-0010
Distribution Limits
Public
Copyright
Other

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