An incompressible viscous flow is contained between two parallel plates separated from each other by distance b. The flow is caused by the movement of the upper plate which has a velocity U, while the bottom plate is fixed. If U = 9.5 m/s and b = 3.2 cm, and there is no pressure gradient in the flow direction. a) Start with Navier-Stokes equations and determine the velocity at the point x = 7 cm and y= 0.56 cm. b) Calculate the magnitude of the vorticity at the same point. c) Calculate the rate of angular deformation at the same point. Work to 4 significant digits. Enter all values using base units or their combinations, i.e. m, m/s, Pa, N. Do not use multiples as e.g. mm, kPa. You can use values with exponents, such as 0.12e3.

6) Air flow though the device shown in figure. Select which set of the following conditions is TRUE assuming incompressible non-viscous steady flow (a) p4 v3 (c) p2>p3; v2 > v3 (e) p4> pl; v4 pl; v1 > v3 (d) p4 vl "OUT

An incompressible viscous flow is contained between two parallel plates separated from each other by distance b. as shown in Figure 1. The flow is caused by the movement of the upper plate which has a velocity U, while the bottom plate is fixed. If U =7 m/s and b= 1 cm, and there is no pressure gradient in the flow direction. A.) Start with Navier-Stokes equations and determine the velocity at the point x = 3 cm and y= 0.41 cm. The value of the velocity is.B.) Calculate the magnitude of the vorticity at the same point. The magnitude value of vorticity. C.) Calculate the rate of angular deformation at the same point. The angular deformation value

(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…