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Incompressible boundary-layer stability analysis of LFC experimental data for sub-critical Mach numbersAn incompressible boundary-layer stability analysis of Laminar Flow Control (LFC) experimental data was completed and the results are presented. This analysis was undertaken for three reasons: to study laminar boundary-layer stability on a modern swept LFC airfoil; to calculate incompressible design limits of linear stability theory as applied to a modern airfoil at high subsonic speeds; and to verify the use of linear stability theory as a design tool. The experimental data were taken from the slotted LFC experiment recently completed in the NASA Langley 8-Foot Transonic Pressure Tunnel. Linear stability theory was applied and the results were compared with transition data to arrive at correlated n-factors. Results of the analysis showed that for the configuration and cases studied, Tollmien-Schlichting (TS) amplification was the dominating disturbance influencing transition. For these cases, incompressible linear stability theory correlated with an n-factor for TS waves of approximately 10 at transition. The n-factor method correlated rather consistently to this value despite a number of non-ideal conditions which indicates the method is useful as a design tool for advanced laminar flow airfoils.
Document ID
19860017742
Acquisition Source
Legacy CDMS
Document Type
Thesis/Dissertation
Authors
Berry, S. A.
(Joint Inst. for Advancement of Flight Sciences Hampton, VA, United States)
Date Acquired
September 5, 2013
Publication Date
July 1, 1986
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.26:3999
NASA-CR-3999
Accession Number
86N27214
Funding Number(s)
PROJECT: RTOP 505-60-21-01
CONTRACT_GRANT: NCC1-24
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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