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Lift on a steady 2-D symmetric airfoil in viscous uniform shear flow

Published online by Cambridge University Press:  28 December 2017

Patrick R. Hammer Open the ORCID record for Patrick R. Hammer [Opens in a new window] ,
Miguel R. Visbal ,
Ahmed M. Naguib  and
Manoochehr M. Koochesfahani
Patrick R. Hammer*
Affiliation:
Department of Mechanical Engineering, Michigan State University, East Lansing, MI 48824, USA
Miguel R. Visbal
Affiliation:
Aerospace Systems Directorate, Air Force Research Laboratory, Wright-Patterson Air Force Base, OH 45433, USA
Ahmed M. Naguib
Affiliation:
Department of Mechanical Engineering, Michigan State University, East Lansing, MI 48824, USA
Manoochehr M. Koochesfahani
Affiliation:
Department of Mechanical Engineering, Michigan State University, East Lansing, MI 48824, USA
*
†Email address for correspondence: [email protected]
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Abstract

We present an investigation into the influence of upstream shear on the viscous flow around a steady two-dimensional (2-D) symmetric airfoil at zero angle of attack, and the corresponding loads. In this computational study, we consider the NACA 0012 airfoil at a chord Reynolds number $1.2\times 10^{4}$ in an approach flow with uniform positive shear with non-dimensional shear rate varying in the range 0.0–1.0. Results show that the lift force is negative, in the opposite direction to the prediction from Tsien’s inviscid theory for lift generation in the presence of positive shear. A hypothesis is presented to explain the observed sign of the lift force on the basis of the asymmetry in boundary layer development on the upper and lower surfaces of the airfoil, which creates an effective airfoil shape with negative camber. The resulting scaling of the viscous effect with shear rate and Reynolds number is provided. The location of the leading edge stagnation point moves increasingly farther back along the airfoil’s upper surface with increased shear rate, a behaviour consistent with a negatively cambered airfoil. Furthermore, the symmetry in the location of the boundary layer separation point on the airfoil’s upper and lower surfaces in uniform flow is broken under the imposed shear, and the wake vortical structures exhibit more asymmetry with increasing shear rate.

JFM classification

Aerodynamics: Aerodynamics
Type
JFM Rapids
Information
Journal of Fluid Mechanics , Volume 837 , 25 February 2018 , R2
Copyright
© 2017 Cambridge University Press 

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