Abstract: There is a great change in pitch moment after the ignition of the scramjet, which has a serious impact on the attitude control of the aircraft.Design idea of two-stage-expansion SERN based on the control of wall pressure distribution was presented. Reference model A and comparison model B which is on the basis of two-stage-expansion were designed under strict geometry restricts.Then, cold-flow static testing and numerical simulation were conducted on the scaled model of B,which agreed well, indicating that the result of numerical simulation was reliable.Comparison is made between model A and model B,indicating that pitch moment difference between cold-state and hot-state of model B decreases by 44.6% than that of model A on the premise that thrust performance descends little for Model B, which effectively reduces the difficulty of the balance of aircraft and verifies the correctness of the design idea. 

Key words: Single-expansion-ramp-nozzle；Wall pressure distribution；Thrust performance

摘要： 提出了基于控制壁面压力分布的分级 单边膨胀喷管(SERN)设计思想。在强几何限制条件下,设计了一个基准模型A,与采用分级膨胀思想设计的模型B进行对比。然后,对模型B喷管进行缩比进行了冷流试验,试验与数值模拟结果吻合良好,说明数值模拟结果可靠。模型A与模型B数值模拟的对比结果表明,模型B喷管在推力性能下降很少的前提下,冷热态俯仰力矩差较模型A下降了44.6%,有效减小了飞行器的配平难度,验证了该设计思想的正确性。 

关键词: 单边膨胀喷管;壁面压力分布;推力性能 