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Study on the influence of canard setting angle and longitudinal position on the sonic boom of supersonic business jet
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Study on the influence of canard setting angle and longitudinal position on the sonic boom of supersonic business jet
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Journal Article
Study on the influence of canard setting angle and longitudinal position on the sonic boom of supersonic business jet
2025
Overview
The aerodynamic layout design for reducing sonic boom intensity was a crucial technology in the development of supersonic business jets. The canard-wing configuration served as a strategic approach to achieving a low sonic boom for supersonic business jets. In this study, the near-field and far-field sonic boom calculation results of the model, as provided by SBPW2, were compared to verify the accuracy of the adopted sonic boom prediction method. A low-sonic-boom configuration featuring a canard wing was proposed for a supersonic business jet, and a comparative analysis was conducted to examine the effects of varying canard wing setting angles and longitudinal positions on the sonic boom results. The canard wing with a positive setting angle effectively generated multiple weak shock waves, thereby reducing the perceived level in decibels on the ground. Specifically, when the canard wing’s setting angle was 3°, the perceived level in decibels reached a minimum of 84.60 PLdB. Additionally, positioning the canard wing further aft enhanced shock wave interference with the wing’s shock wave system, further mitigating the sonic boom. When the longitudinal position was 14 meters, the ground-level perceived loudness was reduced to a minimum of 84.42 PLdB.
Publisher
IOP Publishing
Subject
