CFD Analysis of a High-Speed Scramjet Nozzle with Augmented Shock Expansion

This project designs and analyzes a convergent-divergent SCRAMJET nozzle utilizing Prandtl-Meyer
expansion theory to create efficient, shock-free supersonic flow. The contour of the nozzle was developed
using a MATLAB script based on principles of isentropic expansion and an expanding fan to provide
smooth turning of the flow with no oblique shock generation. The resulting geometry was modelled with
SolidWorks and simulated with ANSYS Fluent via a 2D steady-state simulation with the SST k-?
turbulence model and heat transfer.The CFD simulation results showed a steady increase of the Mach number along the nozzle with even
pressure and temperature gradients, verifying the design efficiency. Of the test cases conducted with
different inlet conditions, the nozzle performed satisfactorily in reducing the losses in pressure while
ensuring a flow of the same quality. The project was successful in verifying the employment of theoretical
expansion fan-based design of the nozzle for the SCRAMJET propulsion system and provides a solid
platform for further development of hypersonic propulsion.