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In this paper a feasibility study on estimation of
heat transfer coefficient and hot gas temperatures of a rocket nozzle is performed by using the
inverse heat conduction method. These parameters are estimated by using transient temperature data
of a simulated experiment, and inverse heat conduction calculations are performed by using the sequential function specification of Beck. The
simulated temperature data are obtained by solving the heat conduction equation numerically,
and applying random errors to the calculated temperatures. Conduction heat transfer in the
nozzle section is assumed to be one dimensional in
the radial direction. Sensitivity coefficients are defined and calculated. Effects of various
parameters, such as amplitude of random errors, number of future temperatures and size of the
time steps in inverse calculations, are plotted and discussed.