Turbulent boundary layer adiabatic wall temperature

At an altitude of 30,000 m the atmospheric pressure is approximately 1200 Pa and the temperature is approximately -4S°C. Assuming a turbulent boundary layer flow over an adiabatic flat plate, plot the variation of the adiabatic wall temperature with Mach number for Mach numbers between 0 and 5. 

We must consider the laminar and turbulent portions of the boundary layer separately because the recovery factors, and hence the adiabatic wall temperatures, used to establish the heat flow will be different for each flow regime. It turns out that the difference is rather small in this problem, but we shall follow a procedure which would be used if the difference were appreciable, so that the general method of solution may be indicated. The free-stream acoustic velocity is calculated from... 

A wind tunnel is to be constructed to produce flow conditions of Mach 2.8 at Ix = -40°C and p = 0.05 atm. What is the stagnation temperature for these conditions What would be the adiabatic wall temperature for the laminar and turbulent portions of a boundary layer on a flat plate If a flat plate were installed... 

Vertical Cavities (0 = 90°) with UH S 2 and W/L a 5. Except in an end region immediately adjacent to the two vertical plates, the flow in a cavity with L H is everywhere parallel to the horizontal walls, with hot fluid in the upper half of the cavity streaming toward the cold plate and cold fluid in the lower half streaming toward the hot plate (only at very high Rayleigh numbers, where turbulent eddies of a scale smaller than H are possible, will this simple flow pattern break down). The plates at temperatures Th and Tc deflect the streams into boundary layers on each vertical surface. The predictions of Bejan and Tien [16] for adiabatic walls are correlated to within 8 percent by their equation... 

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