Application of thin-layer Navier-Stokes equations near maximum liftThe 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 thin-layer Navier-Stokes 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 thin-layer Navier-Stokes 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 Navier-Stokes code with experiment and the viscous-inviscid interaction code is obtained at moderate angles of attack. An unsteady solution is obtained with the thin-layer Navier-Stokes 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.
Document ID
19840035059
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Anderson, W. K. (NASA Langley Research Center Hampton, VA, United States)
Thomas, J. L. (NASA Langley Research Center Hampton, VA, United States)
Rumsey, C. L. (NASA Langley Research Center Low-Speed Aerodynamics Div., Hampton, VA, United States)