Vincente CARDONA, Thierry ANDRE, Victor VERNOUX

DOI Number: N/A

Conference number: HiSST-2025-317

Ramjet and scramjet are engines whose interest in the supersonic and hypersonic applications is always as strong over the world, due to their great specific impulse. However, a high engine efficiency is needed to be truly of interest. To improve the engine efficiency, several parameters may be investigated such as the fuel type, the injection method, the geometry of the engine, among others. In this study, the investigation is focused on the thermal losses in the combustion chamber. This paper presents a preliminary study on an inverse heat conduction method that enables to evaluate the heat flux and thus the thermal losses of a combustion chamber, with a simple wall temperature. As a first use case,
the method was applied to experiments conducted with metallic models, located at the exit of a study ramjet, and suffering important heat fluxes. The mathematical method will be exposed, and applied to experimental results. Results will be discussed, highlighting the advantages and constraints of the method, leading to the next steps of the presented work.

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In Categories: 1.Events, 1.HiSST 2025, Testing & Evaluation
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