Compressible flows are important in aerodynamics and turbomachinery among other applications. In high speed flows around aircraft, the Reynolds numbers are extremely high and turbulence effects are confined to thin boundary layers. The drag consists of two components, frictional drag due to the boundary layer and pressure or form drag which is essentially inviscid in nature; there may also be wave drag due to shocks which may be computed from the inviscid equations provided that care is taken to assure that the second law of thermodynamics is obeyed. If frictional drag is ignored, these flows may be computed using the inviscid momentum Euler equations.
KeywordsMach Number Mass Flux Outer Iteration Incompressible Flow Compressible Flow
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