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对双喉道推力矢量喷管的流动特性和气动性能进行了数值模拟研究,分析了在有无推力矢量情况下,双喉道喷管的主流落压比(Nozzle pressure ratio,NPR)和二次流流量对喷管的气动性能与内部流动特性的影响。研究结果表明,在无推力矢量状态下,双喉道喷管在落压比NPR=3.0~4.0之间具有最优的推力系数和流量系数,分别为0.974和0.935。在有推力矢量状态下,双喉道喷管在NPR=4.0时具有最优的推力矢量角和推力系数,其推力矢量角最高为16.1°。当二次流流量为4%时,推力矢量角为14.6°,推力系数为0.95。随着二次流流量的增加,双喉道喷管的推力矢量角逐渐增加,但是当增加到一定值之后,推力矢量角会逐渐减小。在相同的二次流流量下,随着主喷管落压比的增加,推力矢量角和推力矢量效率逐渐降低。随着主喷管落压比的增加,双喉道喷管的推力系数逐渐升高,在NPR=4.0达到最大值后逐渐降低。流量系数随着主喷管落压比的增加逐渐增大,但是在NPR=4.0以后,流量系数的变化趋于稳定。
The numerical simulation of the flow and aerodynamic performance of a twin-throat thrust vectoring nozzle was carried out. The effects of the Nozzle pressure ratio (NPR) and the secondary pressure Effect of Flow Rate on Aerodynamic Performance and Internal Flow Characteristics of Nozzles. The results show that in the absence of thrust vector, the dual throat lances have the best thrust coefficient and flow coefficient between NPR = 3.0 and 4.0, which are 0.974 and 0.935, respectively. Under the condition of thrust vector, the double throat nozzle has the best thrust vector and thrust coefficient at NPR = 4.0, the maximum thrust vector angle is 16.1 °. When the secondary flow rate is 4%, the thrust vector angle is 14.6 ° and the thrust coefficient is 0.95. As the secondary flow increases, the thrust vector angle of the double throat nozzle gradually increases, but when it increases to a certain value, the thrust vector angle gradually decreases. Under the same secondary flow rate, the thrust vector angle and thrust vector efficiency gradually decrease with the increase of the pressure drop of the main nozzle. With the increase of the rejection ratio of the main nozzle, the thrust coefficient of the double throat nozzle gradually increases and gradually decreases after reaching the maximum value of NPR = 4.0. The flow coefficient gradually increases with the increase of the rejection ratio of the main nozzle, but the change of the flow coefficient tends to be stable after NPR = 4.0.