a smooth flat plate of length 5 m and width 2 m is moving with a velocity of 4 m/s in stationary air of density as 1.25 kg/m³ and kinematic viscosity 1.5 x 10-5 m²/s. determine thickness of the boundary layer at the trailing edge of the smooth plate. find the total drag on one side of the plate assuming that the boundary layer is turbulent from the very beginning.

a smooth flat plate of length 5 m and width 2 m is moving with a velocity of 4 m/s in stationary air of density as 1.25 kg/m³ and kinematic viscosity 1.5 x 10-5 m²/s. determine thickness of the boundary layer at the trailing edge of the smooth plate. find the total drag on one side of the plate assuming that the boundary layer is turbulent from the very beginning.

Principles of Heat Transfer (Activate Learning with these NEW titles from Engineering!)

8th Edition

ISBN:9781305387102

Author:Kreith, Frank; Manglik, Raj M.

Publisher:Kreith, Frank; Manglik, Raj M.

Chapter5: Analysis Of Convection Heat Transfer

Section: Chapter Questions

Problem 5.24P: Engine oil at 100C flows over and parallel to a flat surface at a velocity of 3 m/s. Calculate the...

See similar textbooks

Similar questions

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.
7. A flat plate has a length of 40 cm and width of 1 m. Air, at pressure of 2 atm,temperature of 57 C, and velocity of 3 m/s flows over the plate. Find the thicknessof the boundary layer at x = L.
Note: Don't copy from other websites solution, those are wrong solutions. The trailer travels at U = 39 mi/h. The air is still and has a temperature of 60°F. Assume the surfaces are smooth and flat Consider both laminar and turbulent boundary layers. (Figure 1) Part A :Determine the drag acting on each side of the trailer truck.
Light oil at 75°F flows over a 22-ft-long flat plate with a free-stream velocity of 6 ft/s. Determine the total drag force per unit width of the plate.
The viscous laminar flow of air over a flat plate results in the formation of a boundary layer. The boundary layer thickness at the end of the plate of length L is Delta L . When the plate length is increased to twice its original length. The percentage change in laminar boundary layer thickness at the end of the plate (with respect to Delta L ) is ______
A commercial airplane has a total mass of 70,000 kg and a wing planform area of 150 m2. The plane has a cruising speed of 558 km/h and a cruising altitude of 12,000 m, where the air density is 0.312 kg/m3. The plane has double-slotted flaps for use during takeoff and landing, but it cruises with all flaps retracted. Assuming the lift and the drag characteristics of the wings can be approximated by NACA 23012 , determine (a) the minimum safe speed for takeoff and landing with and without extending the flaps, (b) the angle of attack to cruise steadily at the cruising altitude, and (c) the power that needs to be supplied to provide enough thrust to overcome wing drag.
A commercial airplane has a total mass of 150,000 lbm and a wing planform area of 1700 ft2. The plane has a cruising speed of 625 mi/h and a cruising altitude of 38,000 ft where the air density is 0.0208 lbm/ft3. The plane has double-slotted flaps for use during takeoff and landing, but it cruises with all flaps retracted. Assuming the lift and drag characteristics of the wings can be approximated by NACA 23012, determine (a) the minimum safe speed for takeoff and landing with and without extending the flaps, (b) the angle of attack to cruise steadily at the cruising altitude, and (c) the power that needs to be supplied to provide enough thrust to overcome drag. Take the air density on the ground to be 0.075 lbm/ft3.
A circular sign has a diameter of 50 cm and is subjected to normal winds up to 150 km/h at 10°C and 100 kPa. Determine the drag force acting on the sign. Also determine the bending moment at the bottom of its pole whose height from the ground to the bottom of the sign is 1.5 m. Disregard the drag on the pole.
A small aircraft has a wing area of 37 m2, a lift coefficient of 0.45 at takeoff settings, and a total mass of 4300 kg. Determine the following: The takeoff speed of this aircraft at sea level at standard atmospheric conditions The wing loading The required power to maintain a constant cruising speed of 300 km/h for a cruising drag coefficient of 0.036
A flat plate ( 1.5 m ) long and ( 1.5 m ) wide is towed in water ( ρ = 1000 kg/m3 and ν=1.31 * 10 -6 m2 / s ) in the direction of its length at a speed of ( 20 cm / s ). Determine; a) The skin frictional drag force on both sides of the plate. b) The boundary layer thickness at the end of the plate.
An automotive engine can be approximated as a 0.4-m-high, 0.60-m-wide, and 0.7-m-long rectangular block. The ambient air is at 1 atm and 15°C. Determine the drag force acting on the bottom surface of the engine block as the car travels at a velocity of 120 km/h. Assume the flow to be turbulent over the entire surface because of the constant agitation of the engine block
Evaluate the boundary-layer shape factor, H.