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Amplified crossflow disturbances in the laminar boundary layer on swept wings with suctionSolution charts of the Orr-Sommerfeld equation for stationary crossflow disturbances are presented for 10 typical velocity profiles on a swept laminar flow control wing. The critical crossflow Reynolds number is shown to be a function of a boundary layer shape factor. Amplification rates for crossflow disturbances are shown to be proportional to the maximum crossflow velocity. A computer stability program called MARIA, employing the amplification rate data for the 10 crossflow velocity profiles, is constructed. This code is shown to adequately approximate more involved computer stability codes using less than two percent as much computer time while retaining the essential physical disturbance growth model.
Document ID
19820003518
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Dagenhart, J. R. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
November 1, 1981
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
L-14423
NASA-TP-1902
Accession Number
82N11391
Funding Number(s)
PROJECT: RTOP 534-01-13-14
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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