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采用数值模拟方法,对旋翼下洗气流作用下的排气喷流流动特征进行了研究,分析了旋翼下洗气流速度和排气喷口方向对排气喷流流动以及排气系统引射能力的影响.研究结果表明:排气喷流受到旋翼下洗气流的作用而发生明显的向后机身下方以及旋翼转动方向的偏转,其偏转程度随旋翼下洗气流速度的增大而加剧;当排气喷口向上排气时,排气喷流在旋翼下洗气流作用下的偏转能够形成对后机身表面的撞击,排气系统的引射能力有微弱的降低,引射系数减小约0.01;而当排气喷口斜向上或侧向时,排气喷流对后机身未形成撞击,引射能力得到了一定程度的提升,引射系数最大增大0.12.
The numerical simulation method was used to study the flow characteristics of the exhaust jet under the action of the downwash airflow on the rotor. The effects of the rotor downwash velocity and the exhaust nozzle direction on the exhaust jet flow and the exhaust capability of the exhaust system were analyzed The results show that the deflagration of the exhaust jet flow is affected by the downwash flow of the rotor, and the deflecting degree of the exhaust jet is obviously increased with the increase of the speed of the downwash air flow. When the exhaust gas When the nozzle is exhausted upward, the deflection of the exhaust jet under the action of the scrubbing air under the rotor can form an impact on the rear fuselage surface, and the ejecting capability of the exhaust system decreases slightly, and the ejecting coefficient decreases by about 0.01. When the exhaust nozzle oblique upward or lateral, the exhaust jet on the rear fuselage did not form an impact, injection ability has been improved to some extent, the maximum coefficient of 0.12.