Prediction of Subscale Rocket Engine Acoustic Emissions Using CAA Hybrid Methods

This work presents the results of a numerical study predicting the acoustical emissions induced by the supersonic jets of two different types of nozzle using a CAA (Computational Aeroacoustics) hybrid method. The two types of nozzles studied are a Truncated Ideal Contour (TIC) and a Thrust Optimized Parabola (TOP). To achieve this goal two test series were conducted with the TIC and the TOP nozzle. The results show that the quality of the results depend on the direction in which it is measured. The Agreement between experiments and simulation are good in the areas where the underlying model expects it.