Accurate Prediction of Noise Generation and Propagation

Jet engines are characterized by high-speed free jets. The fact that Federal Aviation Regulations regarding noise levels retard the progress in high speed civil transport planes raises the interest in accurate methods to predict and reduce jet noise. Here, the perturbed flow field of a supersonic jet is solved using an advantageous numerical technique, and the associated noise filed is predicted. Comparisons with experimental results show that this technique is efficient for this kind of problems as it gives accurate
results without requiring a lot of computational power. Due to the nature of the problem, special attention needs to be given to the numerical method as well as the boundary treatments. We observed radial acoustic profiles at different axial distances, where peak intensity is encountered before the decay.