The low sonic boom and aerodynamic optimization with trim constraint of supersonic jet
The abatement of sonic boom noise level is a decisive issue for supersonic transport of next generation. The low sonic boom optimization always make the configuration to a trend of higher swept and longer distribution of the wing along the fuselage，which is unfavorable to the trim and low speed char...
| Main Authors: | , , , |
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| Format: | Article |
| Language: | zho |
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Editorial Department of Advances in Aeronautical Science and Engineering
2024-02-01
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| Series: | Hangkong gongcheng jinzhan |
| Subjects: | |
| Online Access: | http://qktg.shnu.edu.cn/zrb/shsfqkszrb/ch/reader/view_abstract.aspx?file_no=2024-1-38.htm |
| _version_ | 1827324535219683328 |
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| author | HAO Xuan ZHANG Qingqing SU Cheng LIU Fang |
| author_facet | HAO Xuan ZHANG Qingqing SU Cheng LIU Fang |
| author_sort | HAO Xuan |
| collection | DOAJ |
| description | The abatement of sonic boom noise level is a decisive issue for supersonic transport of next generation. The low sonic boom optimization always make the configuration to a trend of higher swept and longer distribution of the wing along the fuselage，which is unfavorable to the trim and low speed characteristics. A civil supersonic transport is researched. A parametric geometry representation method based on class function/shape function transformation（CST）is developed to describe the wing body configuration. The effects of geometry parameters on sonic boom is analyzed by supersonic linearized theory. Based on the above work，the low sonic boom and pitch moment characteristics optimization are taken for the fuselage，wing planform and twists separately and the optimal result is validated by CFD. The numerical simulation results show that compared with the basic configuration，the drag decrease 19 cts（unit of drag coefficient）and the over pressure at near-field is abated obviously without the distinct increase of pitch moment，which bring 5.1 PLdB reduction of loudness on the ground. |
| first_indexed | 2024-04-25T02:15:03Z |
| format | Article |
| id | doaj.art-85b0b76f5e7f4e04bc914b721a8ee03e |
| institution | Directory Open Access Journal |
| issn | 1674-8190 |
| language | zho |
| last_indexed | 2024-04-25T02:15:03Z |
| publishDate | 2024-02-01 |
| publisher | Editorial Department of Advances in Aeronautical Science and Engineering |
| record_format | Article |
| series | Hangkong gongcheng jinzhan |
| spelling | doaj.art-85b0b76f5e7f4e04bc914b721a8ee03e2024-03-07T09:54:37ZzhoEditorial Department of Advances in Aeronautical Science and EngineeringHangkong gongcheng jinzhan1674-81902024-02-01151385010.16615/j.cnki.1674-8190.2024.01.052024015The low sonic boom and aerodynamic optimization with trim constraint of supersonic jetHAO Xuan0ZHANG Qingqing1SU Cheng2LIU Fang3The Second Research Institute, China Academy of Aerospace Aerodynamics, Beijing 100074, ChinaThe Second Research Institute, China Academy of Aerospace Aerodynamics, Beijing 100074, ChinaThe Second Research Institute, China Academy of Aerospace Aerodynamics, Beijing 100074, ChinaThe Second Research Institute, China Academy of Aerospace Aerodynamics, Beijing 100074, ChinaThe abatement of sonic boom noise level is a decisive issue for supersonic transport of next generation. The low sonic boom optimization always make the configuration to a trend of higher swept and longer distribution of the wing along the fuselage，which is unfavorable to the trim and low speed characteristics. A civil supersonic transport is researched. A parametric geometry representation method based on class function/shape function transformation（CST）is developed to describe the wing body configuration. The effects of geometry parameters on sonic boom is analyzed by supersonic linearized theory. Based on the above work，the low sonic boom and pitch moment characteristics optimization are taken for the fuselage，wing planform and twists separately and the optimal result is validated by CFD. The numerical simulation results show that compared with the basic configuration，the drag decrease 19 cts（unit of drag coefficient）and the over pressure at near-field is abated obviously without the distinct increase of pitch moment，which bring 5.1 PLdB reduction of loudness on the ground.http://qktg.shnu.edu.cn/zrb/shsfqkszrb/ch/reader/view_abstract.aspx?file_no=2024-1-38.htmlow sonic boom optimizationsupersonic transportsupersonic linearized theoryparametric geometry representationtrim characteristiccomputational fluid dynamics |
| spellingShingle | HAO Xuan ZHANG Qingqing SU Cheng LIU Fang The low sonic boom and aerodynamic optimization with trim constraint of supersonic jet Hangkong gongcheng jinzhan low sonic boom optimization supersonic transport supersonic linearized theory parametric geometry representation trim characteristic computational fluid dynamics |
| title | The low sonic boom and aerodynamic optimization with trim constraint of supersonic jet |
| title_full | The low sonic boom and aerodynamic optimization with trim constraint of supersonic jet |
| title_fullStr | The low sonic boom and aerodynamic optimization with trim constraint of supersonic jet |
| title_full_unstemmed | The low sonic boom and aerodynamic optimization with trim constraint of supersonic jet |
| title_short | The low sonic boom and aerodynamic optimization with trim constraint of supersonic jet |
| title_sort | low sonic boom and aerodynamic optimization with trim constraint of supersonic jet |
| topic | low sonic boom optimization supersonic transport supersonic linearized theory parametric geometry representation trim characteristic computational fluid dynamics |
| url | http://qktg.shnu.edu.cn/zrb/shsfqkszrb/ch/reader/view_abstract.aspx?file_no=2024-1-38.htm |
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