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Consider a NACA 3408 Airfoil. Calculate and plot the lift coefficient and the drag coefficient as...

Consider a NACA 3408 Airfoil. Calculate and plot the lift coefficient and the drag coefficient as a function of AOA of 3 degrees 6 degrees and 9 degrees by using Vortex Panel Method. For each case use a panel convergence study (increase the number of panels until results are “convergent”. Make comments about your results regarding convergence, AOA limits, etc

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Engineering   Mechanical-Engineering   
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