Unsteadiness boundaries in supersonic flow over double cones

Hornung, H. G.; Gollan, Rowan; Jacobs, Peter A.

doi:10.1017/jfm.2021.203

Cited by 16 publications

(8 citation statements)

References 20 publications

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“…The hypersonic laminar flow over a canonical 25°-55°double cone is investigated using CFD and GSA with varying unit Reynolds numbers. For all cases, no self-sustained inviscid unsteadiness is found, which is consistent with the unsteadiness boundary proposed by Hornung et al (2021). The axisymmetric CFD reveals that the separation region is always terminated by the transmitted shock emanating from the interaction between the oblique and curved shocks induced by the first and second cones.…”

Section: Discussionsupporting

confidence: 86%

“…According to Hornung et al (2021), the pulsation mode is enclosed in the lower and upper boundaries of the second cone angle (θ 2 ) for a given first cone angle (θ 1 ). The lower boundary is located above the shock detachment angle (θ d ) of the second cone with respect to M ∞ .…”

Section: Geometric Configuration and Flow Conditionsmentioning

confidence: 99%

“…In hypersonic laminar flow over a double cone, unsteadiness may occur due to different physical mechanisms. Hornung, Gollan & Jacobs (2021) numerically studied axisymmetric double-cone flows with varying flow parameters. Pulsating unsteadiness was found to be an inviscid phenomenon consistent with the pulsation mode in supersonic spiked-body flows.…”

Section: Introductionmentioning

confidence: 99%

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Three-dimensionality of hypersonic laminar flow over a double cone

2022

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Hypersonic laminar flow over a canonical 25°–55° double cone is studied using computational fluid dynamics and global stability analysis (GSA) with a free-stream Mach number of 11.5 and various unit Reynolds numbers. Axisymmetric simulations reveal that secondary separation occurs beneath the primary separation bubble beyond a critical Reynolds number. The numerical results agree well with existing experiments and the triple-deck theory with the axisymmetric effect on the incoming boundary layer treated by the Mangler transformation. The GSA identifies a three-dimensional global instability that is azimuthally periodic immediately prior to the emergence of secondary separation. The criterion of the onset of global instability in terms of a scaled deflection angle established for supersonic compression corner flows (Hao et al., J. Fluid Mech., vol. 919, 2021, A4) can be directly applied to double-cone flows. As the Reynolds number is further increased, the flow is strongly destabilized with the coexistence of multiple stationary and low-frequency oscillating unstable modes. Direct numerical simulations confirm that the supercritical double-cone flow is intrinsically three-dimensional, unsteady and exhibits strong azimuthal variations in the peak heating.

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Section: Discussionsupporting

confidence: 86%

Section: Geometric Configuration and Flow Conditionsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Three-dimensionality of hypersonic laminar flow over a double cone

2022

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“…Disturbances in the wind tunnel free stream are expected to not bear a discernable influence on the observed unsteady flow behaviour. This is supported by the fact that computational studies of similar shock pulsation/oscillation problems (Feszty et al 2004a,b;Panaras & Drikakis 2009;Hornung et al 2021) are able to reproduce experimental observations with disturbance-free inflow conditions.…”

Section: Discussionmentioning

confidence: 88%

“…The present work aims to understand shock-wave oscillations in a class of problems with two geometric parameters. With the exception of a very recent computational study of the canonical double cone problem by Hornung, Gollan & Jacobs (2021), large-amplitude shock-wave oscillation problems governed by more than a single geometric parameter have not been subject to detailed study. The geometry chosen for this exercise is a forward-facing circular cylinder with a right circular conical forebody (see figure 3a).…”

Section: Introductionmentioning

confidence: 99%