Numerical analysis demonstrates thrust variations in expandable nozzles under supersonic flow, implying design improvements for rocket engines.
The application of an expandable nozzle at flight altitudes up to 40 km is being considered, taking into account the presence of an external supersonic co-current stream. Numerically, in an unsteady formulation, the supersonic turbulent flow of a viscous compressible gas through a nozzle is computed, taking into account the dynamics of the opening of its expanded part. The distribution of pressure, temperature, and the change in axial force (nozzle thrust) over time at different flight altitudes is analyzed. The calculation of the unsteady processes when using an expandable nozzle in dense atmospheric layers, typical for the operation of rocket engines under launch and flight conditions at altitudes up to 40 km, is carried out.
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Kaun et al. (2025) studied this question.
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