Consider a double wedge airfoil with a maximum thickness of 5% chord at angle of attack...

Consider a double wedge airfoil with a maximum thickness of 5% chord at angle of attack = 0 degrees.

a. Determine the approximate chord wise location (x/c) of the maximum thickness that producesthe 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 (t/c) max for each Mach number in your report.

b. Repeat this analysis for an airfoil with 10% maximum thickness. Include the calculated values on your composite plot of part I.a.

c. Discuss what your results say about the effects of Mach number and thickness on minimum drag coefficient.

Expert Solution

samet mamat answered 2 years ago

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