alexa The Research of Supersonic Aircraft Low Sonic Boom Conf
ISSN: 2168-9792

Journal of Aeronautics & Aerospace Engineering
Open Access

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Research Article

The Research of Supersonic Aircraft Low Sonic Boom Configuration Design and Optimizations

Xuan H*, Cheng S and Fang L
China Academy of Aerospace Aerodynamics, Yungang West Road, Beijing, 100074, P. R. China
*Corresponding Author : Xuan H
China Academy of Aerospace Aerodynamics
Yungang West Road, Beijing, 100074, PR China
Tel: +86-13810025289
E-mail: [email protected]
Received: February 27, 2016 Accepted: March 30, 2016 Published: April 03, 2016
Citation: Xuan H, Cheng S, Fang L (2016) The Research of Supersonic Aircraft Low Sonic Boom Configuration Design and Optimizations. J Aeronaut Aerospace Eng 5:165. doi:10.4172/2168-9792.1000165
Copyright: © 2016 Xuan H, et al. This is an open-access article distributed under the terms of the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original author and source are credited.
 

Abstract

High noise level of sonic boom is one of the most important reasons that the supersonic transport can’t be applied to civil aviation broadly. Sonic boom is a complicated problem relating to aircraft configuration design, aerodynamics, acoustics and so on. The traditional sonic boom minimization theory is an inverse design method with single object, which makes it difficult to be applied in multi-objective optimization, effectively. For the low sonic boom configuration optimization, the sonic boom noise level prediction method based on supersonic linear theory was developed. The sonic boom level of a basic configuration of supersonic business jet was computed and the cause of formation of sonic boom was analyzed, based on which the fuse and wing plane wais optimized to decrease the noise level of sonic boom. Compared with the basic configuration, the sonic boom level of optimized configuration decreased distinctively, with the overpressure decreasing 41% and the A-weighted noise level decreasing 7.55 decibel. The aerodynamic characteristics of optimized configuration were computed. Compared with the basic configuration, the drag decreased obviously at the cruise condition without moment change.

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