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The aerodynamic heating is a major problem affecting aerospace vehicles when passing it in the planetary atmosphere. Basically, the aerodynamic heating is the conversion of kinetic energy (velocity) thermal energy (heat) as a result of air flow on the outer surface of the vehicle. When the vehicle reaches the speed of sound higher speeds, forms a next wave of shock to the vehicle, causing significant increase in temperature from the surrounding atmosphere between the shock wave and the outer surface of the vehicle, resulting in heating of the outer surface from the convective heat transfer process.
Evidently, the aerodynamic heating occurs both in launching vehicles into space, as the reentry vehicle in the atmosphere.
However, the reentry is critical, since the vehicles from space, enter the atmosphere at speeds of the order of 8 km / s or greater, and are decelerated to find progressively more dense atmosphere. In ascending flight (on the ground) the vehicle will be progressively increasing flight speed and at the same time as the atmosphere becomes thinner.
The determination of the heat flux on the outer surface of aerospace vehicles is one of the most important parameters in the development of aerospace vehicles. The precise knowledge of this quantity is crucial in the development of the thermal protection system, to ensure the structural integrity of the vehicle during the mission.
Consequently, the main technological challenge for design of thermal protection systems of aerospace vehicles is the characterization of the complexity of the various flight regimes, the various layers of the atmosphere and the thermo-physical phenomena inherent in this aerotermodinâmico aggressive environment, such as flow continuous flow X does not continuous (free molecular flow and transition flow), chemical equilibrium chemical equilibrium X is not ideal gas (thermo-physical constant, or only function of temperature) X real (thermophysical property function of temperature, gas pressure and chemical composition, resulting in dissociation, ionization and / or recombination). Additionally, they must take into account the catalytic and / or ablative outer surface of the material effects of aerospace vehicles.
http://uniespaco.aeb.gov.br/index.php/projetos-de-pesquisa/veiculos-espaciais/19-aerotermodinamica-de-ve
