Consider an airplane flying with a velocity of 60ft/s at a standard sea level conditions. At a point on the wing, the airflow velocity is 70ft/s. Calculate the pressure at this point. Assume the incompressible flow

Find the location of the stagnation point for the flow due to a vortex +I at (2a, 0) and a vortex -25 at (-2a, 0).

A jet of air having velocity V₁ and cross-sectional area A₁ strikes an inclined plate as shown in the figure. Neglect any effects of viscosity. V₁ (a) Find V₂ and V3 in terms of V₁. Note that the pressure is patm everywhere. (b) Because viscous effects are negligible, there is no way for the air to exert a force on the plate in the tangential (z) direction. Using the coordinate system in the figure, find A₂ and A3 in terms of A₁ and 0. (c) For V₁ = 50 m/s, A₁ = 5 x 10-4 m², and 0 = 60°, find the force required to hold the plate in place. Neglect the weight of the plate. Recall that pair = 1.225 kg/m³.

Find the force required to pull a shaft with diameter D, steadily into a sleeve with diameter D, and length L at a velocity of V. The clearance between the shaft and the sleeve is filled with an oil of viscosity μ.