This chapter mainly deal with the properties of two-dimensional airfoils at mach number above 0.3 but below 1, where the compressibil ity must be considered

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Boundary layer(边界层) Although frictional effects in slightly viscous fluid are indeed present, they are confined to a thin layer near the surface of the body, and the rest of the flow can be considered inviscid. (1904, Prandt/)

When is a flow compressible? compressible flow differs from an incompressible one in that significant change happens in the density

《流体动力学》（英文版）lecture 1

HIERARCHY oF 3-D CONEIGURATION CFD METHODS Linear \Singplarity \hethaols-use sucface gridt Non linear \Field \Methods use spoce grids LIFTING- LWE VORTEX-LATCE PANEL FULL EVER NAVIER-STOKES METHOD METHOD

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《流体动力学》（英文版）lecture 5