Transitional hypersonic flow over slender cone/flare geometries
نویسندگان
چکیده
Experiments are performed in a Mach-6 shock tunnel to examine the laminar-to-turbulent transition process associated with sudden increase surface angle on slender body. A cone/flare geometry 5 $^\circ$ frustum and compression angles ranging from 15 allow range of mean flow configurations, spanning an attached shock-wave/boundary-layer interaction fully separated one; unit Reynolds number is also varied modify state incoming second-mode boundary-layer disturbances. Ultra-high-speed schlieren visualizations provide global picture development, supplemented by high-frequency pressure measurements. For compression, unsteady field dominated waves, whose breakdown turbulence generally accelerated (compared straight-cone configuration) encountering change. As increased induce separation, lower-frequency disturbances appear along shear layer that exhibit much larger amplification rates than waves; latter effectively freeze amplitude downstream separation point before rapidly breaking down upon reattachment. The shear-layer become dominant at largest tested. Radiation disturbance energy external consistently observed: this occurs features (flare, or reattachment shocks) for spontaneously waves. combined application spectral proper orthogonal decomposition bispectral analysis allows identification important structures association these prominent nonlinear interactions various configurations.
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ژورنال
عنوان ژورنال: Journal of Fluid Mechanics
سال: 2022
ISSN: ['0022-1120', '1469-7645']
DOI: https://doi.org/10.1017/jfm.2022.769