舰载飞机发动机尾流场数值模拟

为了解舰载机在飞行甲板起飞时发动机尾喷流被喷气偏流板偏转后的流场分布情况，以国外某型舰载机和喷气偏流板为研究对象，采用三维雷诺平均Navier-Stokes方程、k-ε]湍流模型和离散坐标模型（DO模型），借助计算流体动力学（CFD）技术对该舰载机起飞时的尾流场进行了三维数值模拟，空间上采用二阶迎风格式进行耦合求解，时间上采用显式Runge-Kutta方法进行迭代推进，直至流场收敛。结果表明：喷气偏流板对尾流场起到了很好的偏转作用，尾喷流对喷气偏流板背部区域的设备和人员几乎没有影响；尾流场中的高温高压气流主要分布在喷气偏流板与喷口之间的区域，在起飞作业过程中，舰面工作人员和设施要避免进入该区域。所得结果从理论上证明了该喷气偏流板的设计方案能满足舰载机起飞的需求。

Numerical Simulation of the Flowfield of Carrier-Based Aircraft Exhaust Jet

n this paper, the flowfield distribution of the exhaust jet from carrier-based aircrafts is studied, and the case involving deflection by the Jet Blast Deflector（JBD） during launches is particularly investigated. By focusing on the temperature, pressure, and velocity characteristics of the flowfield, this paper numerically simulates the flowfield of the exhaust jet using 3-D Reynolds Averaged Navier-Stokes Equations, the k-ε]Turbulence Method, the Discrete Ordinates Method, and the Computational Fluid Dynamics（CFD） technique. To solve these equations, a two-order upstream scheme and the explicit Runge-Kutta algorithm are applied. The result demonstrates remarkable performance of the JBD as the exhaust jet hardly affects the equipment and staff members behind the deflector. However, there are still several dangerous areas that have very high temperature and pressure such as the region between the deflector panel and the nozzles of aircraft engines. Naturally, any staff member or equipment should be prohibited from entering these areas while aircrafts are taking off. Overall, the results presented here indicate that the design scheme of this JBD fully satisfies the requirements of carrier-based aircrafts during lanches.