For the NACA 65021 airfoil, use XFLRS software in order to perform a 2-D flow analysis...

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For the NACA 65021 airfoil, use XFLRS software in order to perform a 2-D flow analysis at the following flow condition: Reynolds' Number: 2,000,000 Mach No.: 0.45 Angle of attack, Alpha: 3° - Obtain the following: - Transition point locations on the Upper and Lower airfoil surfaces Values of Lift Coefficient (C), Drag Coefficient (CD) and Moment Coefficient (Car) at the Operating Point specified above Minus Cp' versus x graph at the above operating point specified For the NACA 65021 airfoil, use XFLRS software in order to perform a 2-D flow analysis at the following flow condition: Reynolds' Number: 2,000,000 Mach No.: 0.45 Angle of attack, Alpha: 3° - Obtain the following: - Transition point locations on the Upper and Lower airfoil surfaces Values of Lift Coefficient (C), Drag Coefficient (CD) and Moment Coefficient (Car) at the Operating Point specified above Minus Cp' versus x graph at the above operating point specified

Answer rating: 100% (QA)

Here are the results from running the XFLRS analysis software for the NACA ... View the full answer