Air flows parallel to the surface of a smooth flat plate 10 m lon thickness at the leading edge. The Reynolds number at the trailing edge of the plate is 107. Calculate the total drag force due to skin friction on one side of the plate per unit width. Assume that for laminar boundary layer, up to Re, = 5 x 105, the skin friction coefficient is 1.328(Re)-1/2 and for turbulent boundary layer 0.078(Re)-1/5, Take the density of air as 1.2 kg/m² and its dynamic viscosity as 1.8 x 10-5 kg/ms Gr

Air flows parallel to the surface of a smooth flat plate 10 m lon thickness at the leading edge. The Reynolds number at the trailing edge of the plate is 107. Calculate the total drag force due to skin friction on one side of the plate per unit width. Assume that for laminar boundary layer, up to Re, = 5 x 105, the skin friction coefficient is 1.328(Re)-1/2 and for turbulent boundary layer 0.078(Re)-1/5, Take the density of air as 1.2 kg/m² and its dynamic viscosity as 1.8 x 10-5 kg/ms Gr

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 5.50P

See similar textbooks

Similar questions

In the vertical wind tunnel used in paratrooper training, find the wind tunnel free speed required to keep a 75 kg person suspended in the air in a horizontal position. The height of this person is 1.7m and the width is 38cm and the front drag coefficient is around 1. Atmospheric pressure and temperature inside the tunnel are Patm = 85kPa and T = 25C, respectively.
The drag polar equation of a light aircraft in clean configuration is: CD=0.020+0.044C₁2. The aircraft has a wing area of 162.7 ft² and a wing loading of 15.2 psf. It is flying at a velocity of 213 feet per second. Assuming steady level flight and SSLC (p=0.002377 slug/ft³), determine the drag force (in lb, nearest hundredths) being generated by the aircraft.
From Table the drag coefficient of a wide plate normalto a stream is approximately 2.0. Let the stream conditionsbe U∞ and p∞. If the average pressure on the front of theplate is approximately equal to the free-stream stagnationpressure, what is the average pressure on the rear?
The drag coefficient for a car with a frontal area of 26 ft? is being measured in an 8 ft x 8 ft wind tunnel. The density of air under the test conditions is 2.4 x 10 3 slugs/ft, When the air flow rate is, 500,000 ft/min, the drag force on the car was measured to be 170 lb. The drag coefficient under the test conditions is most nearly O 0.30 O 0.32 O 0.28 O 0.34
A square flat plate with sides of length L 2m and a negligible thickness (out of the page) is held stationary in a stream of air that is moving steadily at standard conditions past the plate with a speed U = 10 m/s that is uniform except for the boundary layers. Assume the plate is oriented so that only friction drag is important. Determine the drag coefficient for this plate. Answer: CD, ≈ 0.003 = U L-
Assume air at 20°C and atmospheric pressure on a smooth flat plate with a speed free current of 25 m/s (kinematic viscosity of 1.5x10-5 m2/s and density 1.2 kg/m3). The plate is 4 m long and 1.5 m wide. If the boundary layer is initially laminate and then become turbulent boundary layer with a transition Re of 5x10^5: a) What is the drag coefficient for the plate?b) What is the drag force on the entire plate?c) At what distance x from the plate the profile becomes turbulent.d) What is drag force on the turbulent part?e) What is the drag force on the laminar part?
Consider a 102 mph airflow over a flat plate with a span of 9.7 ft and a planform area of 60 ft2. The boundary layer transitioned from laminar to turbulent. If the total skin friction drag for the laminar section is 0.858 lbs, determine the location of the transition point. Assume SSLC, Provide answer in feet and round off answer to the nearest thousandths.
Based strictly on your understanding of the flat-plate theoryplus adverse and favorable pressure gradients, explainthe direction (left or right) for which airflow past theslender airfoil shape in Fig will have lower total(friction 1 pressure) drag.
A flow of air at 37m/s and at 1.6m from the leading edge. The transition Reynolds number is 3 x 10^5. If the boundary layer is laminar at this point If the boundary layer is turbulent at this point What is the boundary layer thickness in metres? Assuming that the air density is 1.226 kg/m3 and dynamic viscosity is 1.79 x 10-5 kg/ms
A rotary mixer is constructed from two circular disks as shown. The mixer is rotated at 60 rpm in a large vessel containing a brine solution (SG = 1.1, μbrine=1.07×10-3 Pa-s). Determine the appropriate coefficient of drag using Low Reynolds Drag Coefficient. Neglect the drag on the rods and the motion induced in the liquid. Estimate the minimum torque and power required to drive the mixer. only HANDWRITTEN answer needed ( NOT TYPED)
Consider a flat plate as shown below. Freestream air approaches parallel to the plate with the conditions shown. Assume air= 1.63 x 10-5 kg/m-s. Determine; a) the overall drag per unit depth (N/m) for the laminar flow case, b) the overall drag per unit depth (N/m) for the turbulent flow case, and M₁ = 0.4 alt. = 5,000 m L = 0.75 m
1. Zero Lift Drag Coefficient" is a sum of: \C poum |Cp CDOF DoL 1 M