Numerical Prediction of Generation of Axisymmetric Mode Jet Screech Tones at Different Mach Numbers

This paper presents a numerical prediction of the generation of axisymmetric mode jet screech tones, which are a significant contributor to jet noise in the aviation industry. The study uses a Pressure-based solver with a K-е realization turbulence model to simulate the flow field and predict the frequency and amplitude of the tones. The simulations consider factors such as the nozzle geometry, exhaust gas velocity and temperature, and ambient conditions. The predictions are validated through experimental measurements, demonstrating the accuracy of the numerical methods. The screech tone frequencies and sound pressure levels in the near-field are in good agreement with the existing experimental data. The ability to numerically predict the generation of axisymmetric mode jet screech tones is an important tool for designing quieter aircraft engines, improving the comfort and safety of passengers and workers. From the simulated results, it is observed that the intensity of the screech tone is high at lower frequencies and higher Mach numbers.