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  • FLUENT - Flow over an Airfoil- Problem 1

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(b) Make a table of Cl and Cd values obtained for α = 0°, 5°, and 10°. Plot Cl vs.α for the three values of α. Make a linear least­squares fit of this data and obtain the slope. Compare your result to that obtained from inviscid, thin­airfoil theory:

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where α is in degrees.

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