Visualization of curved swept shock wave/turbulent boundary layer interaction in supersonic flow
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SHORT P APER
Yue Zhang • Liang Chen • Hui-jun Tan • Chao Wang • Fei Cheng • Chao Li
Visualization of curved swept shock wave/turbulent boundary layer interaction in supersonic flow
Received: 15 April 2020 / Revised: 30 June 2020 / Accepted: 10 August 2020 Ó The Visualization Society of Japan 2020
1 Introduction Shock wave/boundary layer interaction (SWBLI) is a prominent phenomenon in supersonic and hypersonic inlets that determines their performance and operability. Usually, four types of SWBLIs that may occur in supersonic and hypersonic inlets occur, namely incident shock wave/boundary layer interaction, compressible ramp shock wave/boundary layer interaction, normal shock wave/boundary layer interaction, and three-dimensional shock wave/boundary layer interaction (3D-SWBLI) (Babinsky and Harvey 2011). As a new type of inlet, the inward-turning inlet, which is designed using the streamline tracing technique, demonstrates the theoretical potential to achieve higher efficiencies in comparison with conventional twodimensional structures (Molder and Szpiro 1966; Billig and Kothari 2000). Thus, in recent decades, the flow mechanism in inward-turning inlets led to many research interests in the field. Generally, SWBLIs occur in the leading edges of inward-turning inlets, and they play a key role in inlet flow fields, especially when the inlets are integrated with flight vehicles. The compression surface of an inward-turning inlet is a threedimensional curved compression ramp, where the ramp-induced shock is the curved swept shock. As a result, a SWBLI near the leading edge of an inward-turning inlet is a typical 3D-SWBLI. However, due to the special geometry features of inward-turning inlets, traditional optical flow visualization methods, such as Schlieren methods, cannot clearly observe the flow patterns near the leading edges of inward-turning inlets under the integration condition. To obtain the flow filed of the SWBLI near the leading edge of an inwardturning inlet, the ice-cluster-based planar laser scattering technique (IC-PLS) is used in this paper. The icecluster is well trained with flow and spatial resolution in supersonic turbulent boundary layer, with the change of airflow density in flow field. It becomes inhomogeneous and appears scattering under laser irradiation, which can show the fine structure of the flow field and provide physical basis for flow display (Smith and Smits 1995). Many researchers have demonstrated the applicability of this approach to observe the complex supersonic flow structures (Zhuang et al. 2018; Zhuang et al. 2019; Sheng et al.2018). This paper combines the ice-cluster-based planar laser scattering technique and surface oil flow visualization to obtain the detailed flow patterns in the SWBLI region near the leading edges of the inward-turning inlets under the integration condition.
Y. Zhang (&) L. Chen H. Tan C. Wang F. Cheng C. Li Nanjing University of Aeronautics and Astronautics, Nanjing, Jiangsu, China E-mail: [email protected]
Y. Zhang et al.
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