What is it about?
Development of a simple subsonic boundary layer method suitable to be used coupled with panel methods in order to estimate the aerodynamic characteristics, including viscous drag and maximum lift coefficient, of 3D wings.
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Why is it important?
It does not require viscous-inviscid iterations and it is based on classical integral bi-dimensional boundary layer theory.
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This page is a summary of: A Simple and Robust Subsonic Boundary Layer Method to Be Used with the Panel Method for Wing Calculations Using a Wing Strip Approach, Applied Mechanics and Materials, October 2015, Trans Tech Publications,
DOI: 10.4028/www.scientific.net/amm.798.596.
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