This paper presents a novel approach to design of the supersonic aircraft outer mold line by optimizing a A-weighted loudness-based objective of the sonic-boom signature predicted on the ground. The optimization process uses the sensitivity information obtained by coupling the discrete adjoint formulations for the augmented Burgers equation and computational-fluid-dynamics equations. This coupled formulation links the loudness of the ground boom signature to the aircraft geometry, thus allowing efficient shape optimization for the purpose of minimizing the loudness. The accuracy of the adjoint-based sensitivities is verified against sensitivities obtained using an independent complex-variable approach. The adjoint-based optimization methodology is applied to a configuration previously optimized using alternative state-of-the-art optimization methods and produces additional loudness reduction. The results of the optimizations are reported and discussed.
Sonic-Boom Mitigation Through Aircraft Design and Adjoint Methodology
Journal of Aircraft ; 51 , 2 ; 502-510
01.03.2014
Aufsatz (Konferenz) , Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Sonic-Boom Mitigation Through Aircraft Design and Adjoint Methodology
Online Contents | 2014
|Sonic Boom Mitigation through Aircraft Design and Adjoint Methodology
British Library Conference Proceedings | 2012
|Sonic Boom Adjoint Methodology and Its Applications
British Library Conference Proceedings | 2011
|Sonic Boom Adjoint Methodology and its Applications
AIAA | 2011
|