Aerodynamic Configuration of the HCW Based on the Lifting Body

Abstract

A novel hypersonic aerodynamic configuration of the high-pressure–capturing wing (HCW) based on the lifting body is proposed, and computational fluid dynamics (CFD) is employed to carefully analyze longitudinal and lateral aerodynamic force and flight stability. The major analysis results are as follows. In the longitudinal condition, compared with the lifting body, the HCW configuration shows a 16%–18% rise in lift coefficients while the drag coefficients increase only slightly, so the lift-to-drag ratios are obviously improved, especially when the angle of attack (AOA) is less than 10°, with the lift-to-drag ratios increasing more than 35%. In the lateral condition, lift coefficient, drag coefficient, and lift-to-drag ratio increase by different degrees, and the lateral force and yawing moment presents relatively good linear growth with the angle of side slip. The pressure center coefficient at the theoretical fixed-point of the aircraft is adopted to measure flight stability. Compared with the lifting body, the HCW layout has worse longitudinal stability at a negative AOA and better stability at a positive AOA. The lateral pressure center coefficient grows by about 8% and 5%, respectively, when the AOAs are 0° and 12°. In addition, the leading-edge profile and total length of the capturing wing (CW) are improved according to the characteristics of the flow around the aircraft and the pressure distribution on the lower surface of the CW. Compared with the basic outline, the lift coefficient, drag coefficient, and lift-to-drag ratio of the improved configurations are increased by 7%–27%, 1%–6%, and 6%–25%, respectively. The CW presents more even distribution pressure on the lower surface and a better high-pressure–capturing effect. This study not only further verifies the outstanding lift compensation effect of the HCW but also lays a foundation for the practical design and optimization of this novel aerodynamic configuration.