带尾翼干扰的喷管-后体一体化流场数值模拟

Integrated Nozzle-Afterbody Flowfield Simulation with Empennage Interference

当飞行器处于高亚声速或者是跨声速飞行状态时,其喷管-后体部分一般都会产生相当可观的气动阻力。为研究喷管-后体的气动特性,使用WJ2000显式代数雷诺应力模型和CG K-epsilon 2方程模型对几种单发带尾翼、不带尾翼的喷管-后体模型在外流马赫数Ma=0.9时进行了数值模拟。计算结果表明:尾翼的干扰是有利于减小喷管阻力的;除了无尾翼模型外,尾翼错位布置的喷管-后体模型的总阻力是最小的,这主要是因为同位布置的尾翼本身会产生较大的压差阻力;后体形状对喷管-后体流场也有重要影响。

Aerodynamic drag of nozzle-after body is usually considerable large during the aircraft flight at high subsonic or transonic. The aerodynamic characteristics of several nozzle-after body models for single engine fighter with or without empennage were simulated at Flight Mach number 0.9 using WJ2000 explicit algebraic Reynolds stress model and CG K-epsilon two equation model. The results indicate the interference of the empennage is beneficial to reduce the nozzle drag. Besides the model without empennage, the total drag is lowest for the model with stagger empennage, generate higher pressure drag. In addition, the shape of the empennage is important effect on nozzle0after body flowfield.