Engineering, 06.05.2020 04:17 AnonymousLizard52303

Consider tests of an unswept wing that spans the wind tunnel and whose airfoil section is NACA 23012. Since the wing model spans the test section, we will assume that the flow is two dimensional. The chord of the model is 1.3 m. The test section conditions simulate a density altitude of 3 km. The velocity in the test section is 360 km/h.

a. What is the lift per unit span (N/m) that you would expect to measure when the wing attack angle is 4°?
b. What would be the corresponding section lift coefficient and die moment coefficient (about the quarter-chord point)?

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Consider tests of an unswept wing that spans the wind tunnel and whose airfoil section is NACA 23012...

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