Vortex model for airfoil stall prediction using an interactive boundary-layer method
Vortex model for airfoil stall prediction using an interactive boundary-layer method
- Neue Suche nach: Dini, P.
- Neue Suche nach: Coiro, D.P.
- Neue Suche nach: Bertolucci, S.
- Neue Suche nach: Dini, P.
- Neue Suche nach: Coiro, D.P.
- Neue Suche nach: Bertolucci, S.
An interactive boundary-layer method is developed that is able to predict the aerodynamic performance of airfoils throughout the stall region. This has been achieved by taking into account the net vorticity of the flow in the turbulent separated region on the suction surface. This vorticity is modelled as an inviscid counterclockwise vortex located above the trailing edge, whose direction of rotation is justified by global conservation of angular momentum. An empirical law for the intensity of the vortex as a function of a dimensionless parameter based on flow conditions is presented. Excellent comparisons with measured lift and moment curves and pressure distributions are then presented and discussed.
Dokumentinformationen
Vortex model for airfoil stall prediction using an interactive boundary-layer method
Wirbelmodell zur Vorhersage des Strömungsabreißens an Flügelprofilen mit Hilfe einer interaktiven Grenzschichtmethode
1995
5 Seiten, 9 Bilder, 11 Quellen
Aufsatz (Konferenz)
Englisch
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