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 test case. 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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