Air flows over a 4 meter long flat plate at a velocity of 8 m/s. Using...

Air flows over a 4 meter long flat plate at a velocity of 8 m/s. Using a spreadsheet, calculate the boundary layer thickness and wall shear stress at 0.1 meter intervals along the plate. Do not plot the wall shear stress at x=0. Use a transition Reynolds number of 5 x 10^5 . (You will need to calculate Rex at each location to determine if the laminar or turbulent correlations should be used.) Generate a spreadsheet table that includes columns for the x location, Reynolds number, boundary layer thickness, and wall shear stress. Also include the exact transition location in the x column. At the transition location, calculate both the laminar and turbulent correlations and include both values in your plot. (The solution will have a jump at the transition point.) Plot your results for the boundary layer thickness and wall shear stress on separate plots. Submit a copy of your EXCEL table and the plots you generated. Include a plot title and label the axes with the variable name and units. Use only lines, no symbols, to show your analytical solution.

Solutions

Expert Solution

Density (Kg/m^3)	Velocity (m/s)	Distance (m)	kinematic viscosity of air (m^2/s)	Renolds Number	Boundary layer thickness (m)	Wall shear stress (Pa)
1.2047	8	0.1	1.82E-05	4.39E+04	2.39E-03	0.122108899
1.2047	8	0.2	1.82E-05	8.79E+04	3.37E-03	0.086344031
1.2047	8	0.3	1.82E-05	1.32E+05	4.13E-03	0.070499606
1.2047	8	0.4	1.82E-05	1.76E+05	4.77E-03	0.06105445
1.2047	8	0.5	1.82E-05	2.20E+05	5.33E-03	0.05460876
1.2047	8	0.6	1.82E-05	2.64E+05	5.84E-03	0.049850749
1.2047	8	0.7	1.82E-05	3.08E+05	6.31E-03	0.046152826
1.2047	8	0.8	1.82E-05	3.52E+05	6.75E-03	0.043172015
1.2047	8	0.9	1.82E-05	3.95E+05	7.16E-03	0.040702966
1.2047	8	1	1.82E-05	4.39E+05	7.54E-03	0.038614224
1.2047	8	1.1	1.82E-05	4.83E+05	4.62E-02	0.036817218
1.2047	8	1.1375	1.82E-05	5.00E+05	4.75E-02	0.036205255
1.2047	8	1.1375	1.82E-05	5.00E+05	4.75E-02	0.16596729
1.2047	8	1.2	1.82E-05	5.27E+05	4.96E-02	0.164858278
1.2047	8	1.3	1.82E-05	5.71E+05	5.28E-02	0.164858278
1.2047	8	1.4	1.82E-05	6.15E+05	5.61E-02	0.163104067
1.2047	8	1.5	1.82E-05	6.59E+05	5.93E-02	0.160513797
1.2047	8	1.6	1.82E-05	7.03E+05	6.24E-02	0.158152271
1.2047	8	1.7	1.82E-05	7.47E+05	6.55E-02	0.155984982
1.2047	8	1.8	1.82E-05	7.91E+05	6.86E-02	0.153984513
1.2047	8	1.9	1.82E-05	8.35E+05	7.16E-02	0.152128735
1.2047	8	2	1.82E-05	8.79E+05	7.46E-02	0.150399551
1.2047	8	2.1	1.82E-05	9.23E+05	7.76E-02	0.148781975
1.2047	8	2.2	1.82E-05	9.67E+05	8.05E-02	0.147263474
1.2047	8	2.3	1.82E-05	1.01E+06	8.34E-02	0.14583346
1.2047	8	2.4	1.82E-05	1.05E+06	8.63E-02	0.144482918
1.2047	8	2.5	1.82E-05	1.10E+06	8.92E-02	0.143204107
1.2047	8	2.6	1.82E-05	1.14E+06	9.20E-02	0.141990337
1.2047	8	2.7	1.82E-05	1.19E+06	9.48E-02	0.140835791
1.2047	8	2.8	1.82E-05	1.23E+06	9.76E-02	0.139735377
1.2047	8	2.9	1.82E-05	1.27E+06	1.00E-01	0.138684615
1.2047	8	3	1.82E-05	1.32E+06	1.03E-01	0.137679549
1.2047	8	3.1	1.82E-05	1.36E+06	1.06E-01	0.13671666
1.2047	8	3.2	1.82E-05	1.41E+06	1.09E-01	0.135792814
1.2047	8	3.3	1.82E-05	1.45E+06	1.11E-01	0.134905203
1.2047	8	3.4	1.82E-05	1.49E+06	1.14E-01	0.134051304
1.2047	8	3.5	1.82E-05	1.54E+06	1.17E-01	0.133228842
1.2047	8	3.6	1.82E-05	1.58E+06	1.19E-01	0.132435756
1.2047	8	3.7	1.82E-05	1.63E+06	1.22E-01	0.13167018
1.2047	8	3.8	1.82E-05	1.67E+06	1.25E-01	0.130930413
1.2047	8	3.9	1.82E-05	1.71E+06	1.27E-01	0.130214904
1.2047	8	4	1.82E-05	1.76E+06	1.30E-01	0.129522232

samet mamat answered 1 year ago

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