Experimental and numerical investigations of a scramjet nozzle at various operations
Experimental and numerical investigations of a scramjet nozzle at various operations
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超燃冲压发动机喷嘴在各种操作中的实验和数值研究
DOI：
10.1016/j.ast.2019.105536
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发表时间：
2020
影响因子：
5.6
通讯作者：
Song Guangtao
中科院分区：
文献类型：
--
作者：
Lv Zheng;Xu Jinglei;Yu Kaikai;Song Guangtao
采用实验和数值计算相结合的方法，对超燃冲压发动机非对称喷管在不同工作状态下的性能进行了研究，验证了基于最大推力理论的几何约束下单膨胀斜面喷管（SERN）设计方法的可靠性。皮托管压力测量用于校准设备喷管的出口马赫数。采用纹影照相、静压测量和应变天平相结合的方法，获得了流场特征、沿SERN沿着的压力分布和作用在实验模型上的力。此外，数值计算方法也被应用于获得更详细的流场和SERN的性能。结果表明，实验条件下的流场结构与实际飞行工况下的流场结构有明显差异。由于喷管羽流与外部流动的相互作用，在过膨胀和欠膨胀两种情况下，SERN尾缘的膨胀波之后都出现了激波，但SERN核心流动与外部流动无关。在斜板和斜板前部区域存在两个高压平台，有利于提高推力性能，验证了新SERN设计方法的优越性。数值计算结果与实验结果之间的误差较小，表明了数值方法的可行性。随着飞行马赫数的增加，轴向推力系数沿着减小，升力和俯仰力矩系数增大。与过膨胀工况相比，在某些工况下，欠膨胀流动引起的轴向推力损失更为严重。
The present paper focuses on the study of a scramjet asymmetric nozzle at various operations by applying both experimental and numerical methods, which confirms the reliability of the single expansion ramp nozzle (SERN) design method under geometric constraints based on maximum thrust theory as well. The pitot pressure measurement is used to calibrate the exit Mach number of the facility nozzle. The combination of schlieren photograph, static pressure measurement and strain-gauge balance is employed to obtain the flowfield feature, pressure distribution along the SERN wall and forces acting on the experimental model. Besides, the numerical method is also applied to achieve the more detailed flowfield and performance of the SERN. The results show that the flowfield structure is obviously different between at the experimental conditions and at the actual flight operations. As the interaction of the nozzle plume with the external flow, the shock waves following the expansion waves at the trailing edge of the SERN are all presented at both overexpanded and underexpanded conditions; however, the SERN core flow is independent of the external flow. The existing of two platforms with high-pressure at the front areas of the ramp and cowl are beneficial for improving the thrust performance, verifying the superiority of the new SERN design method. The error of the force between the numerical and experimental results is relatively small, denoting the capability of the numerical method. Furthermore, along with the increase in the flight Mach number, the axial thrust coefficient is decreased, while the lift and pitching moment coefficients are increased. Compared with the cases at the overexpanded operations, the axial thrust loss arising from the underexpanded flow is more serious at certain operations.
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DOI：
10.2514/6.1991-5019
发表时间：
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期刊：
--
影响因子：
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作者：
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通讯作者：
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