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Experimental measurements on an oscillating 70-degree delta wing in subsonic flowA series of low-speed wind tunnel tests on a 70-degree sharp leading-edged delta wing at both static and dynamic conditions were performed to investigate the aerodynamic forces and moments. Forces and moments were obtained from a six component internal strain gauge balance. Static results compared well with the previous experimental findings. Large amplitude dynamic motion was produced by sinusoidally oscillating the model over a range of reduced frequencies. Substantial force and moment overshoots, a delay in dynamic stall, and hysteresis loops between the values of aerodynamnic loads in upstroke and downstroke motion were observed, all of which were strong functions of the reduced frequency. The aerodynamic forces and moments were influenced by the Reynolds number. Asymmetrical vortex bursting produced by nonzero sideslip angle created a complex rolling moment variations with angle of attack.
Document ID
19880053518
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Soltani, M. R.
(Ohio State Univ. Columbus, OH, United States)
Bragg, M. B.
(Ohio State University Columbus, United States)
Brandon, J. M.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 13, 2013
Publication Date
January 1, 1988
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 88-2576
Meeting Information
Meeting: AIAA Applied Aerodynamics Conference
Location: Williamsburg, VA
Country: United States
Start Date: June 6, 1988
End Date: June 8, 1988
Accession Number
88A40745
Distribution Limits
Public
Copyright
Other

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