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采用实验方法,通过在二元收敛-扩张喷管扩张段引入二次流喷射,开展了激波诱导控制的流体推力矢量技术研究.实验过程通过喷管上、下壁面压力测量及出口射流纹影观测,研究了主流压力、二次流喷射压力以及二次流喷嘴几何(缝或孔)对推力矢量喷管性能的影响.同时,结合数值计算方法,对各实验工况下的喷管流场进行数值模拟,获得了实验手段难以得到的流场数据和性能,对实验结果进行了辅助分析.初步研究结果表明:在给定的实验条件下,主流压力越高,喷管推力矢量角越小,同时推力系数越大;二次流压力越高,喷管推力矢量角越大,同时推力系数减小;同孔喷射相比,采用喷缝几何下的上壁面激波诱导分离点更趋于向上游移动,分离点后压升显著,射流穿透能力强,对主流的扰动强烈.
By using the experimental method, the fluid thrust vector technique of shock induced control was introduced by introducing the secondary flow injection in the divergence section of the binary convergent-divergent nozzle.The pressure in the upper and lower wall of the nozzle was measured by the experimental method, The influence of mainstream pressure, secondary injection pressure and secondary nozzle geometry (slit or hole) on the performance of thrust vectoring nozzle was observed and studied.At the same time, with the numerical calculation method, the nozzle flow field The numerical results show that the higher the mainstream pressure and the smaller the nozzle thrust vector angle under the given experimental conditions, the better the experimental results can be obtained.Finally, , While the larger the thrust coefficient; the higher the secondary flow pressure, the greater the nozzle thrust vector angle, while the thrust coefficient decreases; compared with the hole injection, using the geometry of the upper wall shock wave induced separation point tends to be more Upstream movement, after the separation point pressure rise significantly jet penetrating ability, strong disturbance to the mainstream.