Features of panel flutter response to shock boundary layer interactions
Section snippets
Introduction and problem statement
Continued pursuit of lighter-weight, faster vehicles motivates a deeper understanding of aeroelastic behavior in shock-dominated flows. Blevins et al. (2009), Tzong et al. (2010), Quiroz et al. (2012), Zuchowski (2010) and Zuchowski (2012) Classical panel flutter, without impinging shockwaves, is fairly well understood after many years of research. Much of this work is documented in reviews by Dowell (Dowell, 1970, Dowell, 1975) and (Mei et al., 1999). The classical panel flutter problem
Modeling approach
The fluid and structural equations are described along with their respective spatial discretization and time marching techniques. Boundary conditions, domain coupling, and the grid deformation scheme are also discussed. The modeling approach shown below follows that developed previously by Gordnier and Visbal (2002).
Results and discussion
The response of two-dimensional flow over a semi-infinite panel is detailed in Section 3.1, and three-dimensional flow over a square panel in Section 3.2.
Concluding remarks
Impinging oblique shockwaves are found to significantly alter flutter response and onset location for viscous flow with an incoming laminar boundary layer. Thus, this phenomenon is an important consideration when designing high-speed vehicles. Weak impinging shockwaves are shown to reduce flutter amplitude. However, flutter frequency is greatly increased for all configurations with an impinging shockwave. This may have an offsetting impact on fatigue life. Higher shock strengths also reduce the
Declaration of Competing Interest
The authors declare that they have no known competing financial interests or personal relationships that could have appeared to influence the work reported in this paper.
Acknowledgments
This research was conducted with support of the AFRL-OSU Collaborative Center in Aeronautical Sciences, USA (Cooperative Agreement FA8650-13-2-2442). The work of Dr. M. Visbal and Dr. C. Barnes was supported in part by AFOSR under a task monitored by Dr. G. Abate. Simulations were performed using resources provided by the DoD HPCMP at the AFRL, ERDC, and NAVO DSRCs as well as by the Ohio Supercomputer Center. The views and conclusions contained herein are those of the authors and should not be
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2023, International Journal of Mechanical SciencesCitation Excerpt :Consequently, we show here that, the presence of the filament increases the spatial instability of the shock wave pattern and, subsequently, a self-energizing increase of the pressure unsteadiness. This experimental evidence of the turbulence energizing effect of the filament oscillation is in good agreement with the already reported numerical simulations of the flexible flat panel fluttering induced by shock wave boundary layer interaction, which clearly results in an increased level of flow turbulence downstream [70,71]. Finally, the optimization of the air flow has an important effect on the Cofiblas and melt-blowing processes.
Dynamic interaction between shock wave turbulent boundary layer and flexible panel
2022, Journal of Fluids and StructuresCitation Excerpt :Although the standard panel flutter has been studied extensively in the past (Muhlstein et al., 1968; Dowell, 1970, 1973; Mei and Chen, 1999; Hashimoto et al., 2009), Visbal (2012, 2014), for the first time, elucidated the physics of shock induced panel flutter by performing (inviscid and viscous) computations, considering the full Navier–Stokes equations and von Karman plate theory for the flow and structure modeling respectively. Building on his work, Boyer et al. (2018, 2021) further examined the features of SBLI induced panel flutter in 3-D inviscid settings, while (Shinde et al., 2018, 2019c,b) explored a transitional SBLI over a flexible panel. On the other hand, Spottswood et al. (2012, 2013), Brouwer et al. (2021a) conducted several experimental studies to investigate the dynamic response of a flexible panel subjected to high-speed environments including shock impingement. (
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