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Sideslip in a viscous compressible gasBy an analysis of the Navier-Stokes equations it is shown that the aerodynamic coefficients of an infinite rectangular swept wing in an isothermal or adiabatic flow of a compressible gas can be determined from the aerodynamic coefficients of the unswept wing. When the flow is neither isothermal nor adiabatic, a three-dimensional boundary layer theory is developed and applied to the special case of a swept flat plate.
Document ID
19930093949
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Struminsky, V V
Date Acquired
August 16, 2013
Publication Date
April 1, 1951
Report/Patent Number
NACA-TM-1276
Report Number: NACA-TM-1276
Accession Number
93R23275
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
THEORIES - WINGS, SWEEPBACK & SWEEPFORWARD
SIDESLIPPING

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