Spatial Evolution of Mean Flow Properties in Supersonic Boundary Layers of Adiabatic and Isothermal Curved Surfaces Including Shock Interactions

January 8, 2026

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Key Points

To investigate the spatial evolution of mean flow properties in supersonic boundary layers over both adiabatic and isothermal curved surfaces, focusing on shock interactions.
Analyzed supersonic flow conditions on curved surfaces
Examined the behavior of boundary layers under varying thermal conditions
Utilized computational fluid dynamics (CFD) for simulation and analysis
Identified differences in flow characteristics between adiabatic and isothermal surfaces
Described significant shock interactions affecting flow properties
Revealed patterns of mean flow evolution in varying curvature scenarios

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This analysis examines mean flow properties in supersonic boundary layers, indicating significant shock interactions on curved surfaces.

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Junqueira-Junior et al. (2026) studied this question.

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