CFD Investigation of Supersonic Scramjet Exhaust Geometry for Emission Reduction and Sustainable Hypersonic Propulsion

This study employs CFD analysis to optimize the scramjet
exhaust divergent angle with the aim of improving propulsion efficiency
and reducing environmental impact in hypersonic flight. The work uses the
computational fluid dynamics software ANSYS Fluent to simulate the
supersonic flow inside the Scramjet engine. CATIA V5 to make the model
and by using ANSYS to check and design analysis. The performance and
efficiency of a supersonic nozzle under different divergent angles (10, 15,
and 18 degrees) by using a symmetric axis in the two-dimensional model.
Then the scramjet engine's exhaust by changing the angles in different
ways. The degree of the divergent shock wave is coming from the exhaust.
These are generally used to work at a higher speed, typically through the
rocket that uses hydrogen as fuel. The CFD results show that the 15°
divergent angle had the highest outlet velocity (about 720 m/s) and the best
pressure expansion ratio (about 1.32) compared to the 10° and 18° angles.
This means that the nozzle worked better and the flow was more stable.
Keywords: CFD, process innovation, scramjet, lower emission, energy
efficiency