Comparison of Wall Temperatures on Scramjet Inlets at Hypersonic Velocities

Skin frictions produced at high operational speeds generate lots of heat on the surface of the aircrafts. It is very much essential to determine the quantity of the heat produced on the outermost layer of the vehicle during supersonic flight while choosing the material of vehicle manufacturing. Generation of shock waves at the inlets, makes the case more complicated. This work compares the temperatures generated on the surface of scramjet inlet at Mach numbers 5, 6, 7. The commercial CFD tool is used for the simulation. Spalart- Allmaras turbulence model was used to get proper temperature readings across the entire surface. It was found that at higher Mach numbers, the temperatures generated crossed a thousand degrees giving a definite conclusion that materials with low melting points are not suitable for the design of Scramjets.