A computational investigation of aero-optical effects for a shock-boundary layer interaction (SBLI) has been performed in the case of Mach 2 flow into a 20 degree compression ramp. Although over a grid of over 282 million points was used for the initial flow, it was determined that grids which might be acceptable for many SBLI problems was not good enough for the problem of aero-optics. It was found that a combination of grid stretching and misalignment of the shock and grid lead to non-physical density aberrations between the shock and the ramp. The grid system was improved with a new grid that was closer to shock aligned in the far-field and had much more resolution between the shock and the ramp. Preliminary optical results are presented and discussed.
展开▼
