Flow Structure and Heat Flux Distribution of a Backswept Fin Induced Flow Field at M = 6
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Structure and Heat Flux Distribution of a Backswept Fin Induced Flow Field at M = 6 F. Zhanga,*, S. H. Yia, X. W. Xua, H. B. Niua, and X. G. Lua a
College of Aerospace Science and Engineering, National University of Defense Technology, Changsha, 410073 China *e-mail: [email protected] Received September 11, 2019; revised November 20, 2019; accepted December 19, 2019
Abstract–Transient flow structures and surface heat flux distribution of the interfered flow field induced by a backswept fin were obtained by Nano-tracer-based Planar Laser Scattering and temperature sensitive paints under M = 6. Meanwhile, the Reynolds-averaged Navier–Stokes equations with k-ω Shear-Stress Transport turbulence model were solved to simulate the flow field. The numerical results were compared and analyzed with the experimental results. Typical flow structures in interference areas of the swept fin were observed in experiment, including the detached bow shock wave, separation zone, thin boundary layer around the fin and horseshoe vortex, etc. The numerical results were in good agreement with flow visualization images. For heat flux distribution, the experiment observed the high heat flux region near the side of the fin leading edge caused by separated flow and the region with heat flux increase caused by bow shock. The numerical results of the heat flux caused by bow shock were pretty good, but the results of the high heat flux region near leading edge due to reattachment had much difference with the experimental results, which still need further improvement. Key words: hypersonic, backswept fin, flow visualization, heat flux, shock wave DOI: 10.1134/S0015462820040126
As an aerodynamic control component, backswept fin is widely used in subsonic, supersonic and hypersonic aircrafts. However, complex flow phenomena such as shock wave-boundary layer interaction, shock wave and shock wave interference, boundary layer separation and reattachment will exist between the control fin, wing and fuselage under hypersonic conditions, which will lead to severe aerodynamic heating and affect the safety of aircraft seriously. Therefore, researches on flow structures and heat flux distribution of the backswept fin under hypersonic condition are of great guiding significance for the design work and thermal protection of hypersonic aircraft. Researches related to this filed can be traced to 1960s. In early studies, turbulent separation and shockboundary layer interaction caused by rudder-like disturbance were studied by pressure measurement, oil flow and other flow visualization techniques, which emphasized the influence of geometric parameters such as leading edge diameter and swept angle on the size of separation zone [1, 2]. For shock waveboundary layer interactions induced by sharp-fin, the quasi-conical theory which concluded that the flow field displays conical symmetry with respect to an origin [3, 4] was widely accepted. In order to study the relationship between flow structures and heat flux distribution, experimental researches on heat tr
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