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 themaximum thickness that producesthe minimum drag coefficient (cd) atMach numbers of 2, 4 and 6. [Hint: you do not need to investigatelocations ahead of 0.4c]. Include a composite plot of dragcoefficient vs location of (t/c) max for each Mach number in yourreport.
b. Repeat this analysis for an airfoil with 10% maximumthickness. Include the calculated values on your composite plot ofpart I.a.
c. Discuss what your results say about the effects of Machnumber and thickness on minimum drag coefficient.
