04) Define the boundary layer, then find the thickness of boundary layer, shear stress, drag force and coefficient of drag in terms of Re for the velocity profile of laminar boundary layer u/U-4(y/ô)-6(y/ö)³. Calculate the boundary layer thickness and drag force if the air flows over a sharp edged flat plate Im long and 0.5m wide at a velocity 0.9m/s, the air density 1.23 kg/m³ and the kinematic viscosity is 1.46*10-³ m/s².

04) Define the boundary layer, then find the thickness of boundary layer, shear stress, drag force and coefficient of drag in terms of Re for the velocity profile of laminar boundary layer u/U-4(y/ô)-6(y/ö)³. Calculate the boundary layer thickness and drag force if the air flows over a sharp edged flat plate Im long and 0.5m wide at a velocity 0.9m/s, the air density 1.23 kg/m³ and the kinematic viscosity is 1.46*10-³ m/s².

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 5.26P

See similar textbooks

Similar questions

Air flows parallel to a speed limit sign along the highway at speed V = 8.5 m/s. The temperature of the air is 25°C, and the width W of the sign parallel to the flow direction (i.e., its length) is 0.45 m. Is the boundary layer on the sign laminar or turbulent or transitional?
The drag equation for the Gofaster 172 is: D = 0.0003v2A. D is drag in pounds; v is airspeed in feet/second; and A is aircraft frontal area in square feet. At maximum airspeed, D = 140 lbs. How much does max airspeed INCREASE if the fuselage is narrowed such that frontal area A is reduced from 16 ft2 to 14 ft2? Give the answer in ft/sec AND mph. drag is 140 lbs. at maximum airspeed, regardless of frontal area. the question is: what is the INCREASE in max airspeed, not what is the max airspeed.
Fluid Mechanics Problem: A ship is 150 m long and has a wetted area of 5000 m2.If it is encrusted with barnacles, the ship requires 7000 hp to overcome friction drag when moving in seawater at 15 kn and 20oC. What is the average roughness of the barnacles? How fast would the ship move with the same power if the surface were smooth? Neglect wave drag. Note: Treat the ship hull as a flat plate. Use eq. 7.48b to find effective barnacle roughness height.Use equation (7.45) White for the drag coefficient CD = D/.5pV2A , where A is the hull (plate) area, to find the ship velocity for smooth plate.
Air at 20 °C flows at V = 10 m/s over a flat plate of length L= 1.52 m and width W = 2 m. Calculate the boundary layer thickness at the trailing edge of plate and drag force on one side of plate if: a. Surface of plate is smooth.b. Surface of plate is rough. The air properties at 20 °C are: Density, ? = 1.2 kg/m3 and dynamic viscosity, ? = 1.8 x 10^-5 kg/m·s and kinematic viscosity, ν = 1.516×10^-5 m2/s.
One dimension of a rectangular flat plate is twice the other. Air at uniform speed flows parallel to the plate, and a laminar boundary layer forms on both sides of the plate. Which orientation—long dimension parallel to the wind (Fig. a or short dimension parallel to the wind (Figb —has the higher drag? Explain.
Air at 20 °C flows at V = 10 m/s over a flat plate of length L= 1.52 m and width W = 2 m.Calculate the boundary layer thickness at the trailing edge of plate and drag force on one sideof plate if:a. Surface of plate is smooth.b. Surface of plate is rough.The air properties at 20 °C are: Density, ? = 1.2 kg/m3and dynamic viscosity, ? = 1.8x 10-5kg/m·s and kinematic viscosity, ν = 1.516×10-5m2/s. kindly give me the solution of this problem with correct and logical reasoning.
Air at 20 °C flows at V = 10 m/s over a flat plate of length L= 1.52 m and width W = 2 m.Calculate the boundary layer thickness at the trailing edge of plate and drag force on one sideof plate if:a. Surface of plate is smooth.b. Surface of plate is rough.The air properties at 20 °C are: Density, ? = 1.2 kg/m3and dynamic viscosity, ? = 1.8x 10-5kg/m·s and kinematic viscosity, ν = 1.516×10-5m2/s. I got the first solution which was wrong kindly solve it correctly
Air at 20 °C flows at V = 10 m/s over a flat plate of length L= 1.52 m and width W = 2 m.Calculate the boundary layer thickness at the trailing edge of plate and drag force on one sideof plate if:a. Surface of plate is smooth.b. Surface of plate is rough.The air properties at 20 °C are: Density, ? = 1.2 kg/m3and dynamic viscosity, ? = 1.8x 10-5kg/m·s and kinematic viscosity, ν = 1.516×10-5m2/s
Q1/ Boeing 737 - 60 flies at altitude 15000m above sea level with speed 85 m/s and total drag coefficient equal to ( 5) . Find the drag force at this fly condition. Given data IR=287,g=9.81 m/s2 , rho O=0.3648 kg/m2 and wing area = 120m^ ^ 2^ *
Estimate the drag force on the fuselage shown below for a cruising speed of 210 m/s at 10,000m. Hint 1: To calculate the drag force split the fuselage into 4 parts: front hemisphere,cylindrical body, vertical stabilizer, back hemisphere. Model the front and back hemispheres as flow over a sphere. For simplicity treat the cylindrical body and vertical stabilizer as flat plates.Hint 2: Use Cd vs Reynolds number graphs for sphere and flat plate. If your Reynolds number is greater/smaller than the Cd vs Reynolds graph range, you can instead use the greatest/smallest number available on the graph.
The standard sea level value of viscosity coefficient for air is μ = 1.7894×10−5 kg/(m · s) = 3.7373 × 10−7 slug/(ft · s). The wing on a Piper Cherokee general aviation aircraft is rectangular, witha span of 9.75 m and a chord of 1.6 m. The aircraft is flying at cruisingspeed (141 mi/h) at sea level. Assume that the skin-friction drag on thewing can be approximated by the drag on a flat plate of the samedimensions. Calculate the skin-friction drag:a. If the flow were completely laminar (which is not the case in real life)b. If the flow were completely turbulent (which is more realistic)Compare the two results.
We are testing a flat plate of length L = 1.125 m and width W = 0.225 m in a stream of air flowing with a velocity of 20 m/s. In test case 1, the air is flowing parallel to L and in test case 2 air is flowing parallel to W. Find: What portion of the boundary layer flow is laminar in each case? What is the highest laminar boundary layer thickness in each case? Assuming the flow is entirely turbulent over the plate, calculate the drag force in both test cases Take air density as 1.2 kg/m3 and its viscosity as μ=18×10−6μ=18×10−6 N.s/m2.