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通过求解三维雷诺平均的Navier-Stokes(N-S)方程,获得了某大型运输机降落滑跑过程中,在不同滑跑速度下的反推气流扰流流场细节.单台发动机反推气流扰流流场的计算结果表明,在任何状态下,反推气流都不会被发动机重新吸入.飞机/发动机一体化计算结果表明:随着相对来流马赫数的减小,反推气流被发动机重新吸入的可能性不断增大.当相对来流马赫数减小到0.1时,反推气流会被外侧发动机重新吸入,此时,发动机进口截面出现了明显的流场畸变,周向稳态总压畸变指数增加明显.当相对来流马赫数减小到0.05时,两台发动机都会吸入反推气流.当相对来流马赫数减小到0时,反推气流没有被重新吸入发动机,但是反推气流会干扰吸入发动机的自由流,降低自由流的总压,从而也会造成发动机进口的流场畸变.
By solving Navier-Stokes (NS) equation of average three-dimensional Reynolds number, the details of flow field of reverse thrust airflow at different run-off speeds of a large transport aircraft were obtained. Field calculation results show that the anti-thrust gas flow will not be re-inhaled by the engine under any condition.The integrated calculation results of aircraft / engine show that as the relative Mach number decreases, the reverse thrust gas flow is re-inhaled by the engine When the relative flow Mach number decreases to 0.1, the backdraft flow will be re-inhaled by the outer engine, at this time, the inlet section of the engine has obvious flow field distortion and the circumferential steady-state total pressure distortion index increases obviously When both the relative Mach number and the relative Mach number decrease to 0.05, both engines will suck in the thrust reversal flow and when the relative Mach number decreases to 0, the thrust reversal flow is not re-entrained into the engine, but the thrust reversal flow will interfere with inhalation The free flow of the engine reduces the total pressure of the free stream, which can also cause distortion of the flow field of the engine inlet.