Figure 1. Mach number contours.
This case involves the turbulent flow past an airfoil with a single flap.
|Mach||Pressure (psia)||Temperature (R)||Angle-of-Attack (deg)||Angle-of-Sideslip (deg)|
The geometry consists of an airfoil with an airfoil-shaped flap below the trailing edge of the main airfoil.
The computational domain is bounded by the airfoil surfaces and the farfield boundary, which is placed a significantly large distance from the airfoil surfaces. The airfoil surfaces are slip surfaces while exterior boundaries are treated as freestream or farfield boundaries.
The experimental data for this configuration has not yet been obtained.
This case examines the use of overlapping (Chimera) grid topology for two-dimensional domains.
Figure 2. Computational grid showing overlapped grids.
|Study #1||Example||J.W. Slater||Example of Chimera grid.|
Questions or comments about this case can be sent be emailed John W. Slater at the NASA Glenn Research Center.