Numerical Simulation of Flow Over Iced Airfoils
Abstract
This thesis evaluates the performance of an iced NACA 0012 airfoil numerically. The full Navier-Stokes equations are solved using the Beam-Warming algorithm. Steady-state solutions are obtained at a Mach number of 0.12 and a Reynolds number based on chord of 1.41 million, for angles of attack from 2-8 deg. Lift and drag curves obtained from the numerical solutions were compared to experimental data and other numerical results. This comparison showed that the Beam-Warming algorithm provides a good estimate of the lift and drag at angles of attack below stall. Computed lift coefficients were within 11.5% of experimental data. These results were in excellent agreement with other numerical solutions. After stall, however, the code did not predict the expected decrease in lift and the calculated drag coefficient was much lower than the experimental data. Comparison of two local flowfield characteristics with the experimental data was less encouraging. A computed velocity profile was compared to the experimental profile for a station in the separated region on the upper surface. This comparison showed that the computed separation bubble is approximately one half the thickness of the bubble measured experimentally. Flow reattachment location is another measure of the predictive accuracy of the numerical scheme. The reattachment locations from the numerical solutions were 30-40% less than the experimental values. It is concluded that accurate results can be obtained for the global performance parameters.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1988
- Accession Number
- ADA203291
Entities
People
- Larry A. Coleman
Organizations
- Air Force Institute of Technology