TY - GEN
T1 - Planform parameter study and wing twist distribution optimization of a supersonic transport configuration
AU - Fu, Ziyuan
AU - Bai, Junqiang
AU - Liu, Nanxi
AU - Zhang, Yu
AU - Xu, Jiakuan
N1 - Publisher Copyright:
© 2017, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2017
Y1 - 2017
N2 - Aiming at exploring aerodynamic performance of a supersonic transport aircraft under transonic and supersonic condition, several planform parameters, namely inboard sweep angle, outboard sweep angle, aspect ratio and taper ratio, are studied via CFD analysis and wing twist distribution optimization are conducted in this paper. In planform parameters study, arbitrary shape deformation technique is adopted in order to provide computational grid variations in a time efficient manner. Influences of each design variable on aircraft drag performance in transonic and supersonic flow are analyzed and the tendencies are explained and summarized. In wing twist distribution optimization, the drag is minimized by keeping lift fixed. Kriging surrogate model is constructed and on which optimal configuration is searched by multi-objective genetic algorithm. The results of optimized configuration are compared with original configuration to reveal how aerodynamic performance improved. The rules explored and summarized in the present paper can be applied as guideline of supersonic aircraft design.
AB - Aiming at exploring aerodynamic performance of a supersonic transport aircraft under transonic and supersonic condition, several planform parameters, namely inboard sweep angle, outboard sweep angle, aspect ratio and taper ratio, are studied via CFD analysis and wing twist distribution optimization are conducted in this paper. In planform parameters study, arbitrary shape deformation technique is adopted in order to provide computational grid variations in a time efficient manner. Influences of each design variable on aircraft drag performance in transonic and supersonic flow are analyzed and the tendencies are explained and summarized. In wing twist distribution optimization, the drag is minimized by keeping lift fixed. Kriging surrogate model is constructed and on which optimal configuration is searched by multi-objective genetic algorithm. The results of optimized configuration are compared with original configuration to reveal how aerodynamic performance improved. The rules explored and summarized in the present paper can be applied as guideline of supersonic aircraft design.
UR - http://www.scopus.com/inward/record.url?scp=85085847511&partnerID=8YFLogxK
U2 - 10.2514/6.2017-2198
DO - 10.2514/6.2017-2198
M3 - 会议稿件
AN - SCOPUS:85085847511
SN - 9781624104633
T3 - 21st AIAA International Space Planes and Hypersonics Technologies Conference, Hypersonics 2017
BT - 21st AIAA International Space Planes and Hypersonics Technologies Conference, Hypersonics 2017
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - 21st AIAA International Space Planes and Hypersonics Technologies Conference, Hypersonics 2017
Y2 - 6 March 2017 through 9 March 2017
ER -