Reduction of Sonic Boom Loudness Level in Supersonic Aircraft by Optimization of Wing Geometry and Positioning

Abstract

Studying the sonic boom phenomenon is an ongoing interest for researchers and engineers to ensure the possibility of supersonic flights for civil aircraft, allowing faster air travel for everyone. Research in sonic boom reduction was previously done by general aircraft shape optimization and engine design. This research focuses on wing geometry modification and its effects on sonic boom loudness reduction. A supersonic aircraft based on the supersonic airliner concept (SSA) was created to learn how the sonic boom loudness and overpressures change by applying wing geometry sensitivity analyses. The sensitivity analyses include wing geometry changes, wing sweep angle changes, and wing translation while maintaining the same aircraft lift. The volume of the selected aircraft is then matched to the base SSA model for geometric parity. A 2.88 PLdB reduction in sonic boom loudness was achieved while maintaining the same volume and lift as the base SSA model. i I am deeply thankful for the support and encouragement given to me by my supervisor Dr. Joana Rocha, whose research supervision and guidance allowed me to progress this research to completion step-by-step without too much stress. I am grateful for Dr. Rocha's kindness and constant support throughout the difficult times of the Covid-19 pandemic, helping me overcome my sadness and stress of the earlier times during the pandemic. I would also like to thank my family, especially my mother and father, whose constant support and love motivated me to finish this research during difficult times. Despite being overseas, they never forgot to keep in touch and encourage me through my journey to finishing this research.