Unsteady Laminar Boundary-Layer Calculations on Oscillating Configurations Including Backflow. Part 1
By:National Aeronautics and Space Administration (NASA)
Published on 2018-08-06 by Createspace Independent Publishing Platform
A finite difference method has been developed to calculate the unsteady boundary layer over an oscillating flat plate. Low- and high frequency approximations were used for comparison with numerical results. Special emphasis was placed on the behavior of the flow and on the numerical calculation procedure as soon as reversed flow has occurred over part of the oscillation cycle. The numerical method displayed neither problems nor singular behavior at the beginning of or within the reversed flow region. Calculations, however, came to a limit where the back-flow region reached the plate's leading edge in the case of high oscillation amplitudes. It is assumed that this limit is caused by the special behavior of the flow at the plate's leading edge where the boundary layer equations are not valid. Geissler, W. Ames Research Center NASA-TM-84319-PT-1, A-9211, NAS 1.15:84319-PT-1 RTOP 505-31-01
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Book which was published by Createspace Independent Publishing Platform since 2018-08-06 have ISBNs, ISBN 13 Code is 9781724758866 and ISBN 10 Code is 1724758861
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