Physics, 16.07.2019 01:20, lwilliams28
Consider a double wedge airfoil with a maximum thickness of 5% chord at = 0. a. determine the approximate chord wise location (x/c) of the maximum thickness that produces the minimum drag coefficient (cd) at mach numbers of 2, 4 and 6. [hint: you do not need to investigate locations ahead of 0.4c]. include a composite plot of drag coefficient vs location of maximum
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Consider a double wedge airfoil with a maximum thickness of 5% chord at = 0. a. determine the app...
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