An incompressible fluid flows steadily in the entrance region of a two dimensional channel of height 2h. Density of the fluid is 1.24 kg/m3. The uniform velocity at the channel entrance is U1=6.1m/s. The velocity distribution at a section downstream is:

Water at 25˚C is flowing past a long cylinder at a velocity of 1.2 m/s in a large tunnel. Theaxis of the cylinder is perpendicular to the direction of flow. The diameter of the cylinder is0.12 m. What is the force per meter length on the cylinder

(a) A wing section with a chord of c and a span of b is mounted at zero angle of attack in a wind tunnel. A pitot probe is used to measure the velocity profile in the viscous region downstream of the wing section as shown in the figure. The measured velocity profile is u(z) = U∞ - (U/2) cos[TZ/(2w)] for -w ≤ z ≤w. Here, w = 0.02c. Assuming a constant pressure p = po along the streamlines (dashed lines in the figure) and across the wake where the velocity was measured, calculate the friction drag coefficient Cp, of the wing section. U Streamlines u = U_ -- cos 22 2W² +w Viscous wake = -W (b) Consider a thin flat plate at zero angle of attack in an airflow at P∞ = 1.225 kg/m³, T∞ = 288 K and μ∞ 1.7894 x 10-5 kg/m/s. The length of the plate is 2 m and the span is 0.5 m. Assume the boundary layers on the plate are laminar throughout (on the upper and lower surfaces both) where LBL(x)/x = 0.664/√√/Rex applies. The freestream velocity is 100 m/s. Calculate the friction drag (Df) of the first…