1. Using the scenario and values from Prob. 4.34, assume that the flow is completely turbulent. Calculate the boundary layer thickness at the trailing edge and the total skin friction drag. Compare these turbulent results with the laminar results from Prob. 4.34. 2. If the critical Reynolds number for transition is 106 , calculate the skin friction drag for the wing in Prob. 4.34. The wing of the Fairchild Republic A-1 OA twin-jet close-support airplane is approximately rectangular with a wingspan (the length perpendicular to the flow direction) of 17.5 m and a chord (the length parallel to the flow direction) of 3 m. The airplane is flying at standard sea level with a velocity of 200 m/s. If the flow is considered to be completely laminar, calculate the boundary layer thickness at the trailing edge and the total skin friction drag. Assume that the wing is approximated by a fiat plate. Assume incompressible flow.
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