Derivative Convergence (Frames from the Movie)

The following frames depict the derivative of ``density'' at every element in the flow field with respect to ``angle of attack'' for a NACA 0012 Airfoil at ALPHA = 2.0, REY = 9.E6, and FSMACH = 0.6. This is a shock-free testcase. For this example, we were able to get good agreement between derivatives computed by BB, IIM, and one-sided finite differences on the SP2.

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