Experimental Fluid DynamicsNo Access

Visualization and measurement of supersonic jet flow field evolution issuing from a rectangular nozzle with aft-deck

Department of Aerodynamics, College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Yudao Street 29, Nanjing, Jiangsu 210016, China

Key Laboratory of Unsteady Aerodynamics and Flow Control, Ministry of Industry and Information Technology, Nanjing University of Aeronautics and Astronautics, Yudao Street 29, Nanjing, Jiangsu 210016, China

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Chengpeng Wang

Department of Aerodynamics, College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Yudao Street 29, Nanjing, Jiangsu 210016, China

State Key Laboratory of Aerodynamics, China Aerodynamics Research and Development Center, P. O. Box 211, Mianyang, Sichuan 621000, China

E-mail Address: wangcp@nuaa.edu.cn

Corresponding author.

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Wenshuo Wang

Department of Aerodynamics, College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Yudao Street 29, Nanjing, Jiangsu 210016, China

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, and

Keming Cheng

Department of Aerodynamics, College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Yudao Street 29, Nanjing, Jiangsu 210016, China

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https://doi.org/10.1142/S0217979220400925Cited by:0 (Source: Crossref)

This article is part of the issue:

Special Issue — Proceedings of the Eighth International Symposium on Physics of Fluids (ISPF8), 10–13 June, 2019, Xi'an, China

Abstract

An experimental study is reported of supersonic jet surface flow structure visualization and wall shear stress field measurement issuing from a rectangular nozzle with aft-deck. The near-field surface flow structures evolution from over-expansion to under-expansion with the increase of nozzle pressure ratio (NPR) are successfully captured by surface oil flow visualization and shear sensitive liquid crystal coating (SSLCC) technique. The quantitative measurement result of shear stress vector field obtained by SSLCC shows that shear stress directions change significantly across the shock wave and expansion fans, while the magnitudes of shear stress have no obvious changes. Surface streamlines calculated by SSLCC image keep great consistency with the streamlines visualized using oil flow technique, which demonstrates the accuracy and potential application of SSLCC in supersonic jet surface flow visualization.

Keywords:

PACS: 47.40.Ki, 47.40.Nm.

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