Sensitivity Study of Sonic Boom Ground Signature Using Different Axial Distance Step Sizes for Evaluating Near-Field Overpressure
Keywords:Sonic boom, supersonic aircraft, sensitivity analysis
To study the feasibility of supersonic commercial airliners, it is essential to better understand the impact of sonic boom caused by the aircraft. For simplicity, a general supersonic airliner concept by Smith et al. was used to conduct this analysis. Using an aircraft model created using Autodesk’s Fusion 360 CAD program, the effects of the aircraft volume and lift in the near- field of the aircraft was determined using a custom MATLAB script developed in-house. The near-field overpressure was then propagated using NASA’s PC Boom program to determine the ground signature of the airliner. Furthermore, a sensitivity analysis for the geometric and lift properties was conducted. It was determined that an axial step-size of 1.2 m yields the best results for creating the full ground signature propagated by PC Boom and using this step size also has better computation times compared to smaller step-sizes. It was also observed that smaller step sizes for analysis caused noisier data to be produced which may have limited how PC Boom propagates the near-field results as smaller step-sizes have more incomplete ground signatures. Finally, it was determined that a sufficiently large step-size causes the signature propagated by PC Boom to form a different shape compared to step-sizes less than 1.2 m, which should not be considered.
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