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The computational fluid dynamics methods have been applied to simulate the aerodynamic properties of scramjet engine at Mach 4.5. Initially steady state simulations were performed for various cowl position and the obtained results were compared with wind tunnel test data and shown good agreements.
The noticeable points during simulation addressed another important applicability of the way of simulation for transitional mode. However, during this simulation we got many ideas to approach and study the critical problems for evaluating the inlet total and static pressure, temperatures, pressure due to bleed plenum, bleed mass flow rates, etc., and we have now excellent problem-solving capacity for accurate modelling of porous bleeds, boundary layers and shock waves interactions.
The CFD simulation performed for scramjets engine shows a good agreement between simulated data and wind tunnel test data, with following noticeable points:
✔ The terminal shock waves remain at throat at various cowl angles.
✔ Shown constant corrected path even in transition mode at the inlet.
✔ The CFD methodologies developed to be more capable for calculating the accurate total average pressure at the inlet as well as the total pressure recovery.
