Consider a subsonic airflow over a flat plate at zero angle of incidence, in standard atmospheric...

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Consider a subsonic airflow over a flat plate at zero angle of incidence, in standard atmospheric (sea level) conditions. The freestream velocity (parallel to the flat plate) is 10 m/s. The length of the flat plate is 60 cm. Determine: (i) The boundary layer thickness at a distance of x = 16 cm from the leading 4 marks edge. (ii) The values of the wall shear stress and skin friction coefficient at the same 6 marks point (x = 16 cm). (iii) The value of the distance from the leading edge at which you expect 3 marks transition to turbulence to start. (iv) Briefly describe the difference between a laminar and a turbulent boundary 7 marks layer relative to the wall shear stress and the skin friction coefficient, explaining (with the help of suitable sketches) the physical reason behind this difference. Consider a subsonic airflow over a flat plate at zero angle of incidence, in standard atmospheric (sea level) conditions. The freestream velocity (parallel to the flat plate) is 10 m/s. The length of the flat plate is 60 cm. Determine: (i) The boundary layer thickness at a distance of x = 16 cm from the leading 4 marks edge. (ii) The values of the wall shear stress and skin friction coefficient at the same 6 marks point (x = 16 cm). (iii) The value of the distance from the leading edge at which you expect 3 marks transition to turbulence to start. (iv) Briefly describe the difference between a laminar and a turbulent boundary 7 marks layer relative to the wall shear stress and the skin friction coefficient, explaining (with the help of suitable sketches) the physical reason behind this difference.