Date of Award

Spring 5-2016

Access Type

Thesis - Open Access

Degree Name

Master of Science in Aerospace Engineering

Department

Aerospace Engineering

Committee Chair

R.R. Mankbadi

First Committee Member

Anastasios S. Lyrintzis

Second Committee Member

Vladimir V. Golubev

Third Committee Member

Bruce Vu

Abstract

We present here a methodology for using the commercial software ANSYSFLUENT to predict the acoustic field associated with Space-Launch System (SLS). We consider a two-dimensional model of flame deflector, and flame trench. The ANSYS code is then used to simulate the internal flow. Both the steady state case is considered along with other cases where the inflow has a harmonic component. A Ffowcs-Williams Hawking (FWH) surface is then constructed within the computational domain to use the computed flow fluctuations to obtain the acoustic field. The acoustic data was then compared to the experimental data.

When using the ANSYS code for this flow situation, the residuals did not converge but reached an asymptotic oscillatory state. The fluctuation in the residual is too large to consider the computed flow fluctuations to be the sound source. Therefore, the results should be interpreted with caution as a first-attempt preliminary results. However, the calculated sound field qualitatively resembles the experimental observations. This may support the need to address the conversion issue and the need to extend the approach to the realistic three-dimensional case.

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