Q.1 The velocity distribution in a turbulent boundary layer is given by 1/7 What is the displacement thickness &*?
Q: 1. A hydrofoil 0.366 m long and 1.82 m wide is placed in a water flow of 12.9 m/s, with p = 1025.3…
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Q: 1. A hydrofoil 0.366 m long and 1.82 m wide is placed in a water flow of 12.9 m/s, p = 1025.3 kg/m…
A: Given Data⇒ Length of HydrofoilL=0.366 m Widthb=1.82 m Water Flow(U)=12.9ms Densityρ=1025.3kgm3…
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Q: 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…
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A: Given: Mach number = 3.5 T = 20 deg C
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A: Given, U = 40 m/s diameter (d) = 3 cm = 0.03 m Specific Gravity of steel = 7.86 Freebody diagram,…
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Q: 04) Define the boundary layer, then find the thickness of boundary layer, shear stress, drag force…
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Q: Air at 20°C flows at V = 8.5 m/s parallel to a flat plate Fig.. The front of the plate is well…
A: Given that, Temperature of air, T=20 °C,Velocity of air, V=8.5 m/s,Length of plate, L=40…
Q: 1.7 A 90 N rectangular solid block slides down a 30° inclined plane. The plane is lubricated by a 3…
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A: Given:x=72 cm or 0.72 my=54 cm or 0.54 mz=9 cm or 0.09 mρ=1.43 kg/m3v=8.61 m/s
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A: The properties of water at 20 degrees Celsius are: The Reynolds number of the flow is The critical…
Q: 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…
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Q: 04) Define the boundary layer, then find the thickness of boundary layer, shear stress, drag force…
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Q: 04) Define the boundary layer, then find the thickness of boundary layer, shear stress, drag force…
A: Given: The velocity profile, u/U = 4(y/δ)-6(y/δ)^5 The length of plate, L = 1 m The width of plate,…
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Q: The large block shown is x = 72 cm wide, y = 54 cm long, V3 and z = 9.0 cm high. This block is…
A: Given: x=72 cm y=54 cm z = 9 cm v=7.98m/s ρ - 1.43 kg/m3 To find: Drag force
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Q: Q4) Define the boundary layer, then find the thickness of boundary layer, shear stress, drag force…
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Q: 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…
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- Air at 1000C flows at an inlet velocity of 2 m/s between two parallel flat plates spaced 1 cm apart. Estimate the distance from the entrance to the point where the boundary layers meet.Air at 20°C and 1 atm flows at 2 m/s past a sharp flat plate.Assuming that Kármán’s parabolic-profile analysis, , is an accurate, estimate (a) the local velocity u and (b)the local shear stress τ at the position (x, y) = (50 cm, 5 mm).Consider two pressure taps along the wall of a laminar boundary layer as in Fig. The fluid is air at 25°C, U1 = 13.7 m/s, and the static pressure P1 is 2.96 Pa greater than static pressure P2, as measured by a very sensitive differential pressure transducer. Is outer flow velocity U2 greater than, equal to, or less than outer flow velocity U1? Explain. Estimate U2
- In order to avoid boundary layer interference, engineers design a “boundary layer scoop” to skim off the boundary layer in a large wind tunnelFig. . The scoop is constructed of thin sheet metal. The air is at 20°C, and flows at V = 45.0 m/s. How high (dimension h) should the scoop be at downstream distance x = 1.45 m?A heavy sphere attached to a string should hang at an angleθ when immersed in a stream of velocity U, as in Fig. Derive an expression for θ as a function of thesphere and flow properties. What is θ if the sphere is steel(SG = 7.86) of diameter 3 cm and the flow is sea-levelstandard air at U =40 m/s? Neglect the string drag.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 correctlyAir 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/sAir 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.
- 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?Consider a rectangular wing mounted in a wind tunnel. The wing model completely spans the testsection so that the flow sees essentially an infinite wing. The wing has a NACA 2421 airfoil section,a chord of 3.0 m, and a span of 20 m. The tunnel is operated at the following test conditions: P =101,000 N/m2; T = 35° C; V = 50 m/s; and µ = 1.9 * 10 -5 kg/(m s).(a) Determine the operating Reynolds number.(b) Calculate the lift, drag, and moment about the aerodynamic center for an angle of attack of 8 deg andRe=9*106(c) At a Reynolds number of 3 * 106, find the following:1) What is the stalling angle of attack for this airfoil?2) What is the angle of attack for zero lift?3) What is the lift-curve slope?An aluminum cylinder weighing 30 N, 6 cm in diameterand 40 cm long, is falling concentrically through a longvertical sleeve of diameter 6.04 cm. The clearance is fi lledwith SAE 50 oil at 20 ° C. Estimate the terminal (zeroacceleration) fall velocity. Neglect air drag and assume alinear velocity distribution in the oil. Hint: You are givendiameters, not radii.