Sloppy Example
AIAA 2012-4161 original text
Introduction
Many challenges have to be overcome in order to enable sustained hypersonic flights. Among
these, the management of heat loads and of surface temperatures has to be mentioned. The
viscous dissipation of the high enthalpy flow across the hypersonic boundary layer can increase
the flow temperature to levels that exceed the thermo-mechanical limits the available materials.
The surface temperatures can be further increased by the interaction of the dissociated flow with
the vehicle’s surface. Neither current carbon nor ceramic-based materials are able to sustain the
generated extreme surface temperatures for long exposure times. In addition, high pick heat
fluxes are particularly dangerous even if characterized by small characteristic times, due to the
material’s spallation phenomenon. In this harsh environment, the cooling of the exposed
structure, (i.e., surfaces exposed to external flows as well as internal flows as those typical of the
combustor of a scramjet engine) is a stringent requirement. The transpiration cooling technique
allows for a decrease in the heat flux at the wall through the issuing of coolant fluid from a
porous material into the boundary layer. Furthermore, the issuing phenomenon near the wall
generates a protective layer of coolant which favorably acts on preventing active oxidation
phenomena that are known to quickly deteriorate the TPS when particular combinations of
elevated temperatures and low partial pressures of oxygen occur.
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