| Citation: | ZHANG Yuding, XU Jinglei, PAN Ruifeng, et al. Design and numerical simulation of a fluidic vectoring nozzle with thrust reverser[J]. Journal of Aerospace Power, 2024, 39（12）：20220905 doi: 10.13224/j.cnki.jasp.20220905
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Considering the demand of high-speed, high maneuverability and shortening the landing distance of aircraft, a fluidic vectoring nozzle with thrust reverser (BDTN-TR) was proposed by combining the thrust reverser with the bypass dual throat nozzle (BDTN). The two-dimensional numerical simulation results showed that BDTN-TR can shorten the landing distance of aircraft while other performance was basically unchanged. The thrust coefficient and discharge coefficient of BDTN-TR above 0.92 could be obtained in cruise mode. In thrust vectoring mode, due to the pressure drop of separation region in the cavity, the pressure distribution of the mainstream became larger than BDTN, the thrust coefficient of BDTN-TR was above 0.93, the discharge coefficient was above 0.83, and the thrust vectoring angle reached more than 14.4° when the nozzle pressure ratio was within the range of 2 to 10. In thrust reversing mode, the thrust reverser efficiency was above 0.61, and the width of the reverse flow channel played an important role on the aerodynamic performance of the thrust reverser.
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