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Semiempirical method for predicting vortex-induced rolling momentsA method is described for the prediction of rolling moments on a wing penetrating a vortex velocity field generated by a large aircraft. Rolling moments are determined from lifting pressure coefficients computed with an inviscid-flow linear panel method. Two empirical corrections are included to account for the lifting efficiency of an airfoil section and the local stall on the wing. Predicted rolling moments are compared with those from two windtunnel experiments. Results indicate that experimental rolling moments, for which the Reynolds number of the following wing is low, should be interpreted with caution.
Document ID
19860004752
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Allison, D. O. (NASA Langley Research Center Hampton, VA, United States)
Bobbitt, P. J. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 5, 2013
Publication Date
November 1, 1985
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.15:87579
L-15986
NASA-TM-87579
Accession Number
86N14222
Funding Number(s)
PROJECT: RTOP 505-43-90-04
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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