TY - JOUR
T1 - Quasi-three-dimensional high-lift wing design approach considering three-dimensional effects of slipstream for distributed electric propulsion aircraft
AU - CAO, Tianshi
AU - BAI, Junqiang
AU - QIU, Yasong
AU - HAN, Kai
AU - FENG, Shaodong
AU - YU, Shilong
N1 - Publisher Copyright:
© 2024
PY - 2024/11
Y1 - 2024/11
N2 - The efficient utilization of propeller slipstream energy is important for improving the ultra-short takeoff and landing capability of Distributed Electric Propulsion (DEP) aircraft. This paper presents a quasi-three-dimensional (2.5D) high-lift wing design approach considering the three-dimensional (3D) effects of slipstream for DEP aircraft, aiming at maximizing the comprehensive lift enhancement benefit of the airframe-propulsion coupling unit. A high-precision and efficient momentum source method is adopted to simulate the slipstream effects, and the distributed propellers are replaced by a rectangular actuator disk to reduce the difficulty of grid generation and improve the grid quality. A detailed comparison of the 2.5D and 3D configurations based on the X-57 Mod Ⅳ is performed in terms of flow characteristics and computational cost to demonstrate the rationality of the above design approach. The optimization results of the high-lift wing of the X-57 Mod Ⅳ show that the aerodynamic performance of the landing configuration is significantly improved, for instance, the lift coefficient increases by 0.094 at the angle of attack of 7°, and 0.097 at the angle of attack of 14°. This novel approach achieves efficient and effective design of high-lift wings under the influence of distributed slipstream, which has the potential to improve the design level of DEP aircraft.
AB - The efficient utilization of propeller slipstream energy is important for improving the ultra-short takeoff and landing capability of Distributed Electric Propulsion (DEP) aircraft. This paper presents a quasi-three-dimensional (2.5D) high-lift wing design approach considering the three-dimensional (3D) effects of slipstream for DEP aircraft, aiming at maximizing the comprehensive lift enhancement benefit of the airframe-propulsion coupling unit. A high-precision and efficient momentum source method is adopted to simulate the slipstream effects, and the distributed propellers are replaced by a rectangular actuator disk to reduce the difficulty of grid generation and improve the grid quality. A detailed comparison of the 2.5D and 3D configurations based on the X-57 Mod Ⅳ is performed in terms of flow characteristics and computational cost to demonstrate the rationality of the above design approach. The optimization results of the high-lift wing of the X-57 Mod Ⅳ show that the aerodynamic performance of the landing configuration is significantly improved, for instance, the lift coefficient increases by 0.094 at the angle of attack of 7°, and 0.097 at the angle of attack of 14°. This novel approach achieves efficient and effective design of high-lift wings under the influence of distributed slipstream, which has the potential to improve the design level of DEP aircraft.
KW - Distributed electric propulsion aircraft
KW - High-lift wing design
KW - Quasi-three-dimensional optimization
KW - Three-dimensional effects of slipstream
KW - Ultra-short takeoff and landing
UR - http://www.scopus.com/inward/record.url?scp=85205262644&partnerID=8YFLogxK
U2 - 10.1016/j.cja.2024.06.034
DO - 10.1016/j.cja.2024.06.034
M3 - 文章
AN - SCOPUS:85205262644
SN - 1000-9361
VL - 37
SP - 300
EP - 316
JO - Chinese Journal of Aeronautics
JF - Chinese Journal of Aeronautics
IS - 11
ER -