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Multi-element airfoil viscous-inviscid interactionsSubsonic viscous-inviscid interactions for multi-element airfoils are predicted by iterating between inviscid and viscous solutions until the performance coefficients converge. Inviscid flow is modelled by using distributed source-vortex singularities on configuration surface panels. Viscous effects are calculated by an existing laminar separation bubble model and a NASA-Lockheed boundary layer-wake method. Numerical formulations and example calculations are presented.
Document ID
19790023986
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Gross, L. W. (McDonnell Aircraft Co. Saint Louis, MO, United States)
Date Acquired
September 3, 2013
Publication Date
January 1, 1979
Publication Information
Publisher: NASA
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-159125
Accession Number
79N32157
Funding Number(s)
CONTRACT_GRANT: NAS1-15369
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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