Abstract
In order to establish the heat transfer model of solid rocket motor nozzle expansion section based on roughness wall, an appropriate heat transfer model is proposed, and the heat transfer model is established by the combination of experiment and numerical calculation. Results demonstrate that: 1) with the increase of the depth of temperature measuring points in different sections, the temperature increases and the corresponding time response accelerates. With the increase of the expansion ratio of temperature measuring sections, the temperature decreases. 2) The overall trend between the calculation results and the experimental measurement results is relatively consistent, which indicates that the numerical calculation method established in this paper has certain applicability and can accurately reflect the heat transfer characteristics of solid rocket motor nozzle expansion section based on real roughness wall. 3) The establishment of heat transfer model is completed using the segmented method, and the error between Nu calculated by the proposed heat transfer model and Nu calculated by numerical calculation is controlled within 21% and 13% in the first and second segments respectively. It shows that the heat transfer model established in this paper has certain rationality and reliability.
Published Version
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