Vortex model for airfoil stall prediction using an interactive boundary-layer method

Conference · Fri Sep 01 00:00:00 EDT 1995

OSTI ID:93002

Dini, P ^[1]; Coiro, D P ^[2]; Bertolucci, S

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1. Carleton College, Northfield, MN (United States). Dept. of Physics and Astronomy
2. Universita di Napoli (Italy). Dipartimento di Progettazione Aeronautica

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.

• OSTI ID: 93002
• Report Number(s): CONF-950116-; ISBN 0-7918-1294-4; TRN: IM9537%%45
• Resource Relation: Conference: 1995 American Society of Mechanical Engineers (ASME) energy sources technology conference and exhibition, Houston, TX (United States), 29 Jan - 1 Feb 1995; Other Information: PBD: 1995; Related Information: Is Part Of Wind energy 1995. SED-Volume 16; Musial, W.D.; Hock, S.M. [eds.] [National Renewable Energy Lab, Golden, CO (United States)]; Berg, D.E. [ed.] [Sandia National Labs., Albuquerque, NM (United States)]; PB: 298 p.
• Country of Publication: United States
• Language: English

Related Subjects

17 WIND ENERGY
WIND TURBINES
PERFORMANCE
AIRFOILS
AERODYNAMICS
VORTEX FLOW
FLOW MODELS
FORECASTING