Question: 7. Consider the double-wedge profile airfoil shown below. The thickness ratio is 0.04, the free stream Mach number is 2.0 and the angle of

7. Consider the double-wedge profile airfoil shown below. The thickness ratio is 0.04, the free stream Mach

7. Consider the double-wedge profile airfoil shown below. The thickness ratio is 0.04, the free stream Mach number is 2.0 and the angle of attack is 2.. Use linearized theory to calculate the lift coefficient, the drag coefficient, and give the aerodynamic center.

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SOLUTION To calculate the lift coefficient drag coefficient and the aerodynamic center using linearized theory we need some additional information about the airfoil geometry However I can provide you ... View full answer

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