the transition point between laminar and turbulent flow A. the boundary layer gets thinner and the speed increases B. the boundary layer thickens and the speed decreases

Q2.A

You are working for a glider manufacturer and have been asked to analyse the laminar boundary layer at a certain point on the smooth wing. The velocity profile at this point, ?(?), is given by:? =3A?C" −2A?C# +?A?C+? ?! δ δ δwhere δ is the boundary-layer thickness and ?$ is the velocity at the edge of the boundary layer. ? and ? are constants.Determine the values of ? and ? such that the primary boundary condi9ons for the velocity profile are sa9sfied. Is it necessary to apply any auxiliary boundary condi9ons?Evaluate the boundary-layer shape factor, H.At the point of separa9on, the wall shear stress goes from posi9ve to nega9ve. Thus, show that the boundary layer at this loca9on is on the point of separa9ng.Show that the pressure on the wing surface is increasing with downstream distance. Is this consistent with your calcula9ons showing that the boundary layer is approaching separa9on? Explain your reasoning.

Water at 10°C flows over a 1.1-m-long flat plate with a velocity of 0.55 m/s. If the width of the plate is 2.5 m, calculate the drag force acting on the top side of the plate. (Water properties at 10°C are: ? = 999.7 kg/m3, ? = 1.307 × 10−3 kg/m·s.) (a) 0.46 N (b) 0.81 N (c) 2.75 N (d ) 4.16 N (e) 6.32 N

Show that the pressure on the wing surface is increasing with downstream distance. Is this consistent with your calculations showing that the boundary layer is approaching separation? Explain your reasoning.

a. If the velocity distribution for the laminar boundary layer over a flat plate is given by :- ** (²) ² - 21 + A₂ x U A₁ + A₂ x Determine the form of the velocity profile by using the necessary boundary conditions. After that by using the Von-Karman integral momentum equation find an expression in terms of the Reynolds number to evaluate 1- Boundary Layer Thickness Force 2-Wall Shear Stress 3-Drag 5- Displacement Thickness + A₁ x 4- Local and Average Skin Friction Coefficients 6- Momentum Thickness 7- Energy Thickness

The turbulent boundary layer can be considered to consist of four regions. Which choice is not one of them? (a) Buffer layer (b) Overlap layer (c) Transition layer (d ) Viscous layer (e) Turbulent layer

The resultant of the pressure and wall shear forces acting on a body is measured to be 430 N, making 30° with the direction of flow. Determine the drag and the lift forces acting on the body.

Wind flows over a flat plate of length L = 25 mm and width W = 8 mm. The plate is maintained at a constant temperature of 32 °C on both sides. using an electric heater generating heat at a rate of Q = 0.5 W which is dissipated to air from both sides of the plate. Consider the temperature of the wind/air as 20 °C and assume that the wind speed does not exceed 100 m/s. The properties of air at this temperature are given as; specific heat capacity Cp = 1.005 kJ/kg-K, thermal conductivity k = 0.0253 W/m-K, Density p = 1.19 kg/m³, and kinematic viscosity v = 1.522 x 10 5 m²/s.