[Nick R]

Hey guys,


I'm going to simulate flow past a round cylinder at a range of low to high (sub to super-sonic ) Mach numbers. I've seen the publisheddata plots for the drag over a range of Mach numbers for comparison, but something doesn't make sense to me. Since drag coefficient is defined as Drag/(0.5densityVelocity^2Area) and since we're dealing with supersonic flow,then density and velocity must be different for each flow case, ie the dynamic pressure would vary. Then how is it fair to compare the drag coefficient for these ranges of Mach number?