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在落压比为4～60范围内,对两个不同下腹板长度的单边膨胀喷管模型进行了试验研究,得到了其壁面静压分布,并对4种不同下腹板长度的喷管模型进行了数值模拟研究,获得了总体性能参数.结果表明:在整个落压比范围内,喷管流动都呈现很强的三维特征,而且在高落压比条件下上膨胀面两侧边气流出现了横向分离.喷管轴向推力系数峰值随下腹板长度增大而增加,峰值对应的落压比也逐渐增大并趋近设计点.在落压比为30～80范围内,轴向推力系数随着下腹板长度增大而增加,在设计点轴向推力系数的最大值和最小值相差约1.8%;在特定低落压比条件下,较短下腹板长度的喷管具有高的轴向推力系数.气流矢量角随下腹板长度增加而增大,在设计点最大值和最小值分别为6.03°和-1.83°.
The uniaxial expansion nozzle model with two different lower web lengths was experimentally studied in the range of pressure drop ratio of 4 ~ 60. The static pressure distribution of the wall was obtained. And the nozzle models of four different lower web lengths The numerical simulation is carried out and the overall performance parameters are obtained.The results show that the nozzle flow shows a strong three-dimensional characteristic over the entire pressure ratio, and the gas flows on both sides of the upper expansion surface appear under high pressure ratio The peak axial thrust coefficient peak increases with the increase of the length of the web, the corresponding drop ratio of the peak also gradually increases and approaches the design point.In the pressure ratio of 30 ~ 80 range, axial thrust The coefficient increases with the length of the lower web, and the difference between the maximum value and the minimum value of the axial thrust coefficient at the design point is about 1.8%. At the specific low pressure ratio, the nozzle with shorter lower web length has a high axial Thrust coefficient The airflow vector angle increases with the length of the lower web, and the maximum and minimum values at the design point are 6.03 ° and -1.83 °, respectively.