Navier-Stokes calculation of a supersonic projectile. This filtered result is different than those discussed in the paper Shock Detection From Computational Fluid Dynamics Results. This scheme collects all cells that are above the test function into regions. These segments are tested to see if there are more than a minumum number of cells and the pressure gradient for the entire collection is greated than a specified value.

Data courtesy of Walt Sturek and David Haroldsen at ARL.