NASA NTRS · 19930093949
Sideslip in a viscous compressible gas
Abstract
By 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.
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Struminsky, V V. 1951-04-01. Sideslip in a viscous compressible gas. https://ntrs.nasa.gov/citations/19930093949
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