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Comparison of analytical and experimental steadyand unsteady-pressure distributions at Mach number 0.78 for a high-aspect-ratio supercritical wing model with oscillating control surfacesThe unsteady aerodynamic lifting surface theory, the Doublet Lattice method, with experimental steady and unsteady pressure measurements of a high aspect ratio supercritical wing model at a Mach number of 0.78 were compared. The steady pressure data comparisons were made for incremental changes in angle of attack and control surface deflection. The unsteady pressure data comparisons were made at set angle of attack positions with oscillating control surface deflections. Significant viscous and transonic effects in the experimental aerodynamics which cannot be predicted by the Doublet Lattice method are shown. This study should assist development of empirical correction methods that may be applied to improve Doublet Lattice calculations of lifting surface aerodynamics.
Document ID
19850007388
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Mccain, W. E.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 5, 2013
Publication Date
January 1, 1984
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-84589
NAS 1.15:84589
Accession Number
85N15697
Funding Number(s)
PROJECT: RTOP 505-33-53
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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