Hysteresis in flow past a NACA 0012 airfoil
type: Item
instance of: scholarly article
title: Hysteresis in flow past a NACA 0012 airfoil
zbMATH Open document ID: 1031.76028
DOI: 10.1016/S0045-7825(01)00382-6
author: Sanjay Mittal
author: Priyank Saxena
published in: Computer Methods in Applied Mechanics and Engineering
publication date: 2002-06-16T00:00:00Z
review text: The authors perform computations of two-dimensional flow past a stationary NACA 0012 airfoil with progressively increasing and decreasing angles of attack. The incompressible Reynolds averaged Navier-Stokes equations in conjunction with Baldwin-Lomax model for turbulence closure are solved using stabilized finite element formulation. Beyond a certain angle of attack the flow stalls with a sudden loss of lift and increase in drag. Hysteresis in aerodynamic coefficients is observed for a small range of attack angle close to the stall angle. This is caused by the difference in the location of separation point of the flow on the upper surface of the airfoil during increasing and decreasing angles of attack. With increasing angle, the separation point moves gradually towards the leading edge. With decreasing angle, the motion of separation point away from the leading edge is abrupt.
reviewed by: Titus Petrila
Mathematics Subject Classification ID: 76M10
Mathematics Subject Classification ID: 76D05
Mathematics Subject Classification ID: 76F10
zbMATH DE Number: 1756425
zbMATH Keywords: turbulence closure
zbMATH Keywords: hysteresis
zbMATH Keywords: stabilized finite element formulation
zbMATH Keywords: NACA 0012 airfoil
zbMATH Keywords: incompressible Reynolds averaged Navier-Stokes equations
zbMATH Keywords: Baldwin-Lomax model
zbMATH Keywords: angle of attack
zbMATH Keywords: separation point
MaRDI profile type: Publication
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description: scientific article; zbMATH DE number 1756425