Application of thinlayer NavierStokes equations near maximum lift
Abstract
The flowfield about a NACA 0012 airfoil at a Mach number of 0.3 and Reynolds number of 1 million is computed through an angle of attack range, up to 18 deg, corresponding to conditions up to and beyond the maximum lift coefficient. Results obtained using the compressible thinlayer NavierStokes equations are presented as well as results from the compressible Euler equations with and without a viscous coupling procedure. The applicability of each code is assessed and many thinlayer NavierStokes benchmark solutions are obtained which can be used for comparison with other codes intended for use at high angles of attack. Reasonable agreement of the NavierStokes code with experiment and the viscousinviscid interaction code is obtained at moderate angles of attack. An unsteady solution is obtained with the thinlayer NavierStokes code at the highest angle of attack considered. The maximum lift coefficient is overpredicted, however, in comparison to experimental data, which is attributed to the presence of a laminar separation bubble near the leading edge not modeled in the computations. Two comparisons with experimental data are also presented at a higher Mach number.
 Publication:

AIAA, Aerospace Sciences Meeting
 Pub Date:
 January 1984
 Bibcode:
 1984aiaa.meetS....A
 Keywords:

 Airfoil Profiles;
 Angle Of Attack;
 Boundary Layer Equations;
 High Reynolds Number;
 Lift Augmentation;
 NavierStokes Equation;
 Aerodynamic Stalling;
 Compressible Flow;
 Computational Fluid Dynamics;
 Eddy Viscosity;
 Euler Equations Of Motion;
 Separated Flow;
 Fluid Mechanics and Heat Transfer