@article{HUANG2023, 
author = {Shuai HUANG and Jinglei XU and Kaikai YU and Yangsheng WANG and Ruifeng PAN and Kuangshi CHEN and Yuqi ZHANG},
title = {Numerical study of a trapezoidal bypass dual throat nozzle},
year = {2023},
journal = {Chinese Journal of Aeronautics},
volume = {36},
number = {3},
pages = {42-62},
keywords = {Bypass dual throat nozzle, Infrared stealth performance, Mixing performance, Trapezoidal cross-sections, Thrust vectoring},
url = {https://www.sciopen.com/article/10.1016/j.cja.2022.11.015},
doi = {10.1016/j.cja.2022.11.015},
abstract = {Bypass Dual Throat Nozzle (BDTN) is a novel type of fluidic thrust vectoring nozzle. To improve the infrared stealth performance of BDTN, a nozzle based on BDTN is proposed and numerically simulated. Each cross-section along the x-axis of the novel nozzle becomes a trapezoid, which is named “BDTN-TRA.” The main numerical simulation results show that BDTN-TRA can produce a thrust vectoring angle when the upper or lower bypass valve is open. The angle difference between the two conditions mentioned above is usually approximately 1°–2°. Even if the two bypasses are closed, BDTN-TRA can produce a small thrust vectoring angle at around 3°–5°. When the sidewall angle increases from 60° to 90°, the thrust coefficient and thrust vectoring angle under each work condition usually decrease. A larger aspect ratio indicates better performance. As the aspect ratio increases over 7.2, the performance of BDTN-TRA is quite close to that of BDTN with rectangular cross-sections at the same aspect ratio. These features will benefit the control and trimming for future aircraft design, especially for the flying wing layout aircraft. Last but not least, BDTN-TRA has a more extraordinary mixing performance compared with BDTN. The distributions of static temperature and axial velocity along the x-axis of BDTN-TRA with sidewall angle of 60° decrease faster than those of BDTN. When the total temperature of the inlet equals 1600 K, the static temperature difference between BDTN-TRA with sidewall angles of 60° and 90° is over 360 K at twice the length of the nozzle downstream of the nozzle exit, which is the reflection for excellent infrared stealth for the fighter.}
}