Volume 39, Number 1, February 2021
|Page(s)||17 - 26|
|Published online||09 April 2021|
Influences of distributed propulsion system parameters on aerodynamic characteristics of a BLI-BWB UAV
School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China
Focusing on the aerodynamic characteristics of the blended wing body (BWB) aircraft with boundary layer ingestion(BLI) distributed propulsion system; the influences of propulsion system parameters under the condition of cruise and takeoff are studied. Firstly, based on the momentum source method (MSM), the NASA ducted propeller model is simulated, which verifies the reliability of the numerical method in this paper. Then, by using the method of structural grid and S-A turbulence model to solve the Reynolds averaged Navier-Stokes (RANS) equation, the aerodynamic characteristics of the BLI UAV model with D80 ducted fan in cruise state are numerically calculated. It is proved that the advantage of the BLI distributed propulsion system is superior in increasing lift. And the aerodynamic characteristics of the BLI UAV with different propulsion system parameters are compared. At last, the aerodynamic effect of ducted fan thrust on the BLI UAV is carried out. The results show that, due to the suction function of the BLI distributed propulsion system, the air flow velocity near the BWB fuselage is effectively accelerated, and the flow along the spanwise is restrained, which improves the lift coefficient about 16% and lift-to-drag ratio about 10%. Under the condition of equal thrust, the D80 ducted fan brings larger load of the propeller, which makes the static pressure at the inlet and outlet smaller. Compared with D150 ducted fan, the lift-to-drag ratio is increased by 15%. When aircraft takes off, increasing the thrust of the ducted fan can reduce the possibility of flow separation on the upper surface of the fuselage, which is conducive to the safety.
Key words: UAV / distributed propulsion / boundary layer ingestion(BLI) / blended wing body(BWB) / ducted fan / momentum source method / aerodynamic characteristics / lift-to-drag ratio / simulation
关键字 : 分布式动力 / 边界层吸入 / 翼身融合 / 涵道风扇 / 动量源方法 / 气动特性
© 2021 Journal of Northwestern Polytechnical University. All rights reserved.
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