A highly polished chromium flat plate is placed in a high-speed wind tunnel to simulate flow over the fuselage of a supersonic aircraft. The air flowing in the wind tunnel is at a temperature of 0?C, a pressure of 3500 N/m2, and a velocity parallel to the plate of 800 m/s. What temperature is the adiabatic wall temperature in the laminar region and how long is the laminar boundary layer?GIVENHigh speed air flow over a flat plateAir temperature (T??) = 0?C = 273 KAir pressure = 3500 N/m2Air velocity (U??) = 800 m/sASSUMPTIONSSteady stateTransition to turbulence occurs at Rex = 105The air behaves as an ideal gasRadiation heat transfer is negligible because of the low emissivity of theplate

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Transion Alr U=800 m/s T.=0°C Le