ACTA AERONAUTICAET ASTRONAUTICA SINICA >
A high lift-to-drag ratio unconventional blended-wing-body aerodynamic configuration with swallow tail
Received date: 2023-09-21
Revised date: 2023-09-28
Accepted date: 2023-11-27
Online published: 2023-12-13
Supported by
National Natural Science Foundation of China(12372288)
The future development of advanced high-performance aircraft not only raises an urgent demand for significant improvement in aerodynamic performance such as the lift-to-drag ratio and maximum lift coefficient， but also faces more stringent design constraints and requirements of various disciplines such as overall/structural/stealth/flight control. According to the overall top-level aircraft design and engineering applications， we conduct an unconventional blended-wing-body swallow tail aerodynamic layout design optimization and performance analysis based on the new blended-wing-body integration design idea of large effective volume stealth fuselage， high lift and large aspect ratio stealth natural laminar flow wing， and efficient simultaneous geometric and aerodynamic integration design of fuselage/wing， and rear body/swallow tail. The results of CFD calculation and the wind tunnel test show that at Mach number Ma=0.194， Reynolds number Re=5.2 ×105， the maximum lift-to-drag ratio is about 31.2， and the aerodynamic performance is excellent. Meanwhile， the basic longitudinal/transverse aerodynamic characteristics and swallow tail rudder effect can meet the flight control requirements. The transition infrared measurement test results show that the free transition position is in good agreement with the laminar airfoil/wing aerodynamic design theory. The surface flow separation wire test results show that the swallow tail is significantly affected by the wing downwash flow， with further research to be conducted in the future.
Liu LIU , Xianhong XIANG , Yufei ZHANG , Haixin CHEN , Chuang WEI , Jian ZHU , Pu YANG . A high lift-to-drag ratio unconventional blended-wing-body aerodynamic configuration with swallow tail[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2024 , 45(6) : 629630 -629630 . DOI: 10.7527/S1000-6893.2023.29630
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