variavel0=<b>Fábio Yukio Kurokawa</b> - kurokawa@dem.feis.unesp.br Universidade Estadual Paulista
<b>Edson Luiz Zaparoli</b> - zaparoli@ita.cta.br Instituto Tecnológico da Aeronáutica
<b>Antonio João Diniz</b> - diniz@dem.feis.unesp.br Universidade Estadual Paulista
<b>Abstract.</b> The problems related to the transmission of heat in high-speed flows had become important in the last years due aerodynamic heating caused in the launched as well as in the re-entry and in the propulsion system nozzles. Due the sonic as well as hypersonic speeds have been needed to thermally protect the structure and its content of the heating caused by the aerodynamic flow. Among the more used thermal protection systems are those employing the ablative materials. The ablative thermal protection analysis is complex because involves heat and mass transfer, chemical reactions and so on, and could, moreover, occur partial or total loss of mass in the structure boundary. In order to mathematically model the ablative thermal protection problem in a body of blunt geometry, a partial differential equations system with non-linear boundary conditions is presented. Solutions of ablatives problems are presented in the literature through several methods and techniques. One of this methods, the Generalized Integral Transformed of Technique (G.I.T.T.), have been proving to be a valuable tool to solve this class of problems where the boundary is not known a priori. The partial differential equations system will be evaluated analytically through the application of G.I.T.T., resulting in an ordinary differential equations system of infinite order. The external surface is subject to a prescribed unsteady heat flow. In this work the coupled ordinary differentiate equations solution system is seek originated from the analytic development. This system presents explicitly the interested variables: the thickness of the ablative layer and the ablative material loss rate for the atmosphere.
<b>Keywords.</b> aerodynamic flow, ablation, geometry blunt, generalized integral transformed, thermal protection.