A hybrid design approach combining the method of characteristics (MoC) for initial axisymmetric nozzle design with a geometric transformation to create an asymmetric supersonic profile is developed. The resulting asymmetric flow field is analyzed by means of 3D CFD simulations using FVM ANSYS Fluent and the k–ω SST turbulence model, and is compared to FDM available solutions. A mesh sensitivity study confirming grid independence is performed. The results demonstrate a smooth supersonic expansion to the Mach number 1.4, with less than 5% pressure deviation from the MoC predictions, attributed to solver differences. Additionally, pressure gradients along the cross-sections decrease from 5% at the throat to 0.5% at the exit, confirming effective flow homogenization. It is also found that the axisymmetric nozzle outperformed the asymmetric wedge in the thrust coefficient (6% higher) and the mass flow (34% greater), but the wedge design shows superior pressure uniformity, advantageous for integrated airframes. The methodology provides a practical framework for preliminary asymmetric nozzle design, highlighting trade-offs between the thrust efficiency and the geometric adaptability.
Dai et al. (Sun,) studied this question.