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Turbulent boundary layers over nonstationary plane boundariesMethods of predicting integral parameters and skin-friction coefficients of turbulent boundary layers developing over moving-ground-planes are evaluated using test information from three different wind tunnel facilities at the NASA Langley Research Center. These data include test information from the VSTOL tunnel which is presented for the first time. The three methods evaluated were: (1) relative integral parameter method, (2) relative power law method, and (3) modified law of the wall method. Methods (1) and (2) can be used to predict moving-ground-plane shape factors with an expected accuracy of + or - 10%. They may also be used to predict moving-ground-plane displacement and momentum thicknesses with lower expected accuracy. This decrease in accuracy can be traced to the failure of approximations upon which these methods are based to prove universal when compared with VSTOL tunnel test results.
Document ID
19760024363
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Roper, A. T.
(Rose-Hulman Inst. of Tech. Terre Haute, IN, United States)
Date Acquired
September 3, 2013
Publication Date
September 1, 1976
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
ME-76-1-ATR
NASA-CR-148861
Accession Number
76N31451
Funding Number(s)
CONTRACT_GRANT: NSG-1258
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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