The drag coefficient for the car is CD�� = 0.28, and the projected area into the 20∘C∘C airstream is 2.5 m2m2. At this temperature ρa�� = 1.202 kg/m3kg/m3. (Figure 1) Determine the power the engine must supply to maintain a constant speed of V� = 160 km/hkm/h

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.

Determine the lift coefficient of a supersonic aerofoil, approximated by a flat plate. It is flying at Ma 3.4 at an angle of attack of 7°. Assume the fluid to be air as a perfect gas with k=1.4.

The oil tanker has a smooth surface area of 4.7(1033) m2m2 in contact with the sea. The velocity of the ship is 2 m/sm/s. Suppose that L� = 350 mm . Take ρ� = 1030 kg/m3kg/m3 and μ� = 1.14(10−3−3) N⋅s/m2N⋅s/m2. ( Determine the friction drag on its hull. Express your answer to three significant figures and include the appropriate units. Determine the power required to overcome this force. Express your answer to three significant figures and include the appropriate units.