The development of an unsteady boundary-layer method using a finite difference scheme is presented. Cebeci-Smith zero equations model is implemented and Keller box scheme has been used. A low-pass filtering function is applied to eliminate numerical instability near the wall. Boundary-layer thickness, displacement thickness, velocity profiles and drag coefficient are calculated. Comparisons of this method with analytical models, CFD simulations and experimental data show good agreement

Development of an Unsteady Boundary-Layer Method

Pandin, Enrico
2015/2016

Abstract

The development of an unsteady boundary-layer method using a finite difference scheme is presented. Cebeci-Smith zero equations model is implemented and Keller box scheme has been used. A low-pass filtering function is applied to eliminate numerical instability near the wall. Boundary-layer thickness, displacement thickness, velocity profiles and drag coefficient are calculated. Comparisons of this method with analytical models, CFD simulations and experimental data show good agreement
2015-04-24
unsteady, boundary, airfoil, laminar, cebeci, smith, flugge, lotz, falkner, skan
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Utilizza questo identificativo per citare o creare un link a questo documento: https://hdl.handle.net/20.500.12608/19660