Assume that you have an aerofoil of given surface roughness in a flow at a free stream velocity of 245 ???. How far from the leading edge the transition will take place. Given that Recr= 5x10^5.
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Assume that you have an aerofoil of given surface roughness in a flow at a free stream velocity of 245 ???. How far from the leading edge the transition will take place. Given that Recr= 5x10^5.
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- fast.PART A -5 For Air Assume: v=1.46×10 m²/s and p =1.225 kg/m³ Question A1 A flat plate with unit width is placed in a uniform steady two-dimensional flow of air with negligible pressure gradient. The velocity distribution of the boundary layer forming on either side of this plate has been given as: U /Us = 2.0(y/ 8) - (y/8)2.0, where U = 10 m/s. 1- Find and expression for the boundary layer thickness as a function of Rex. 2- At x=1.0 m calculate the shear stress corresponding to the points y=0.0,3.0 and 10.0 mm. 3- Calculate the boundary layer displacement and momentum thicknesses at x=1.0m. By using the calculated momentum thickness determine the drag force acting on one side of the plate between its leading edge and x = 1.0m. 4- At x=1.0m, calculate the mass flow rate through the boundary layer (mkg/s per unit width of the plate). What is the corresponding mass flow rate if the flow was inviscid (m; kg/s per unit width of the plate)? 5- By using appropriate equation (s) explain how the…a. If the velocity distribution for the laminar boundary layer over a flat plate is given by :- ** (²) ² - 21 + A₂ x U A₁ + A₂ x Determine the form of the velocity profile by using the necessary boundary conditions. After that by using the Von-Karman integral momentum equation find an expression in terms of the Reynolds number to evaluate 1- Boundary Layer Thickness Force 2-Wall Shear Stress 3-Drag 5- Displacement Thickness + A₁ x 4- Local and Average Skin Friction Coefficients 6- Momentum Thickness 7- Energy Thickness
- Consider the boundary layer flow = 1 - (1 − 2)¹5, 0In the flow of air at 20°C and 1 atm past a flat plate inFig. , the wall shear is to be determined at position x bya floating element (a small area connected to a strain-gageforce measurement). At x = 2 m, the element indicates ashear stress of 2.1 Pa. Assuming turbulent flow from the leadingedge, estimate (a) the stream velocity U, (b) the boundarylayer thickness δ at the element, and (c) the boundary layervelocity u, in m/s, at 5 mm above the element.A flat plate with sharp leading edge is placed in the test section of a low-speed wind tunnel. The working section of the wind tunnel has been designed to produce a region of constant free stream velocity (i.e., for x < 1.0 m, U̟ = 27.0 m/s), followed by a region of decelerating flow (i.e., for x 2 1.0, U̟ = A'(1 – m/s, Figure Q1. Wind Tunnel Wal - 27.0 0". for xS 1.0 m m/s. for x2 1.0 m For 1.0m Flat Plate L. Figure Q1 U, is the freestream air velocity, x is the streamwise position in meter, Lref is a reference length equal to 10 m and x = 0 corresponds to the leading edge of the flat plate. 1- Determine the constant A and its dimension.Assume that you have an aerofoil of given surface roughness in a flow at a free stream velocity of 245 ???. How far from the leading edge the transition will take place. Given that ???? = 5∗ 105.SEE MORE QUESTIONSRecommended textbooks for youElements Of ElectromagneticsMechanical EngineeringISBN:9780190698614Author:Sadiku, Matthew N. O.Publisher:Oxford University Press
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