%0 Book Section
%4 dpi.inpe.br/plutao/2013/05.31.19.10.30
%2 dpi.inpe.br/plutao/2013/05.31.19.10.31
%@doi 10.1051/eucass/201304167
%@isbn 978-2-7598-0876-2
%F lattes: 1394917692174274 1 HinckelSavoPati:2013:DeThLo
%T Determination of thermal load in film cooled bipropellant thrust chambers by an inverse method
%D 2013
%A Hinckel, José Nivaldo,
%A Savonov, Roman I.,
%A Patire Jr., Heitor,
%@affiliation Instituto Nacional de Pesquisas Espaciais (INPE)
%@affiliation Instituto Nacional de Pesquisas Espaciais (INPE)
%@affiliation Instituto Nacional de Pesquisas Espaciais (INPE)
%@electronicmailaddress hinckel@dem.inpe.br
%@electronicmailaddress rsavonov@dem.inpe.br
%@electronicmailaddress heitor@dem.inpe.br
%E Wheeler, C. J.,
%B Progress in Propulsion Physics
%I Torus Press
%C Moscou
%V 4
%P 167-184
%K thermal load, bipropellant thrust chambers, film cooled.
%X A method to obtain the heat load on the internal wall of a rocket thrust chamber using an inverse problem approach is described. According to the classical approach, the heat load on the internal wall of the chamber is assumed as the product of a heat transfer coefficient and the temperature difference of adiabatic wall temperature and local wall surface temperature. The time-dependent temperature distribution of the external wall of the thruster chamber is used to obtain empirical curve fittings to the temperature profile of the near wall flow field (adiabatic wall temperature) and the heat transfer coefficient profile. The applicability of the method is verified by applying it to three different problems; a model problem, an analytical solution, and a set of experimental data.
%@language en
%3 eucass4p167.pdf
%U http://dx.doi.org/10.1051/eucass/201304167
%O This is an Open Access article distributed under the terms of the Creative Commons Attribution License 2.0, which permits
%O unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.