超声速喷管起动过程激波结构演化特征

王成鹏; 杨锦富; 程川; 王文硕; 徐培; 杨馨; 焦运; 程克明

doi:10.11729/syltlx20180143

超声速喷管起动过程激波结构演化特征

doi: 10.11729/syltlx20180143

南京航空航天大学航空学院, 南京 210016

基金项目:

国家自然科学基金项目 51776096

国家自然科学基金项目 51476076

空气动力学国家重点实验室研究基金项目 SKLA20180304

详细信息

作者简介:
王成鹏(1978-), 男, 山东人, 副教授。研究方向:高速空气动力学, 实验空气动力学。通信地址:江苏省南京市秦淮区御道街29号航空学院342信箱(210016)。wangcp@nuaa.edu.cn

通讯作者:
王成鹏, E-mail:wangcp@nuaa.edu.cn

中图分类号: V211.7
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- 被引次数: 0
出版历程
- 收稿日期: 2018-10-18
- 修回日期: 2018-12-18
- 刊出日期: 2019-04-25

Research on evolution of starting shock in a supersonic nozzle

College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

摘要

摘要: 通过改变进出口压比，对马赫数2.7的二维对称拉瓦尔喷管流动进行了试验研究，给出了超声速喷管起动过程中的激波结构演化特征。在试验过程中，固定喷管喉道出口面积比，改变喷管上下游压比，使喷管起动激波从喉道发展到喷管出口处，逐渐过渡到设计工况。在起动激波向下游发展的过程中，喷管内流动经历了教科书上给出的理论过程：喉道正激波、扩张段内正激波、喷管出口马赫反射、喷管出口规则反射、设计工况等；但由于附面层的存在，每一个过程与无粘情况下的激波示意图都有所不同。比如，试验中捕捉到的激波串在向下游的移动过程中，出现的由λ型激波向Х型激波的转变，以及激波串非对称现象的出现等。基于纹影和剪切敏感液晶摩阻显示技术获得了起动激波串的首道激波的三维特征。
- 超声速喷管 /
- 起动激波 /
- 激波附面层干扰 /
- 激波串 /
- 激波反射
Abstract: The starting process of the flow in a Mach 2.7 supersonic nozzle is experimentally investigated. The starting shock moves from the throat to the exit of the nozzle when the incoming total pressure is gradually increased. The flow in the nozzle undergoes the process of normal shock at the throat, normal shock at the expansion duct, oblique shock at the expansion duct, Mach reflection at the exit of the nozzle, regular reflection at the exit of the nozzle and the design conditions. The transformation from the Mach reflection to the regular reflection is observed based on the experimental result of schlieren and PIV. The three-dimensional flow structure of the leading shocks of the shock train has been rebuilt by using the schlieren image system and the shear-sensitive liquid crystal technology.
- supersonic nozzle /
- starting shock /
- shock/boundary layer interaction /
- shock train /
- shock reflection

HTML全文

图 1 南京航空航天大学NH-1风洞扩压器的激波串

Figure 1. Shock train in NH-1 wind tunnel diffuser

下载: 全尺寸图片幻灯片

图 2 拉瓦尔喷管中气体流动状态理论示意图

Figure 2. Schematic illustration of flow state in Laval nozzle

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图 3 试验模型示意图

Figure 3. Schematic illustration of test model

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图 4 下壁面沿程压力分布曲线

Figure 4. Pressure distribution along the bottom wall

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图 5 规则反射和马赫反射纹影结果

Figure 5. Schlieren images of Mach reflection and regular reflection

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图 6 马赫反射和规则反射示意图

Figure 6. Mach reflection and regular reflection

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图 7 与图 5(b)纹影对应的PIV流场

Figure 7. PIV image corresponding to Fig. 5(b)

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图 8 p_b/p₀=0.633喷管内纹影图和下壁面压力分布

Figure 8. Schlieren image and pressure distribution on the bottom wall under the condition of p_b/p₀=0.633

下载: 全尺寸图片幻灯片

图 9 喷管内纹影图和下壁面压力分布

Figure 9. Schlieren image and pressure distribution on the bottom wall under the conditions of p_b/p₀=0.509 and p_b/p₀=0.436

下载: 全尺寸图片幻灯片

图 10 喷管内纹影图和下壁面压力分布

Figure 10. Schlieren image and pressure distribution on the bottom wall under the conditions of p_b/p₀=0.329 and p_b/p₀=0.301

下载: 全尺寸图片幻灯片

图 11 p_b/p₀=0.240喷管内纹影图和下壁面压力分布

Figure 11. Schlieren image and pressure distribution on the bottom wall under the condition of p_b/p₀=0.240

下载: 全尺寸图片幻灯片

图 12 起动斜激波串位于扩压段时首道斜激波三维特征

Figure 12. 3D characteristics of the leading oblique shocks when the starting shock train locates in the diffuser

下载: 全尺寸图片幻灯片

参考文献(16)

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