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An airfoil theory of bifurcating laminar separation from thin obstacles

Published online by Cambridge University Press:  26 April 2006

C. J. Lee  and
H. K. Cheng
C. J. Lee
Affiliation:
Depatment of Aerospace Engineering, University of Southern California, Los Angeles, CA 90089-1191, USA
H. K. Cheng
Affiliation:
Depatment of Aerospace Engineering, University of Southern California, Los Angeles, CA 90089-1191, USA
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Abstract

Global interaction of the boundary layer separating from an obstacle with resulting open/closed wakes is studied for a thin airfoil in a steady flow. Replacing the Kutta condition of the classical theory is the breakaway criterion of the laminar triple-deck interaction (Sychev 1972; Smith 1977), which, together with the assumption of a uniform wake/eddy pressure, leads to a nonlinear equation system for the breakaway location and wake shape. The solutions depend on a Reynolds number Re and an airfoil thickness ratio or incidence τ and, in the domain $Re^{\frac{1}{16}}\tau = O(1)$ considered, the separation locations are found to be far removed from the classical Brillouin–Villat point for the breakaway from a smooth shape. Bifurcations of the steady-state solution are found among examples of symmetrical and asymmetrical flows, allowing open and closed wakes, as well as symmetry breaking in an otherwise symmetrical flow. Accordingly, the influence of thickness and incidence, as well as Reynolds number is critical in the vicinity of branch points and cut-off points where steady-state solutions can/must change branches/types. The study suggests a correspondence of this bifurcation feature with the lift hysteresis and other aerodynamic anomalies observed from wind-tunnel and numerical studies in subcritical and high-subcritical Re flows.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 216 , July 1990 , pp. 255 - 284
Copyright
© 1990 Cambridge University Press

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