Effect of Görtler-like vortices of various intensity on heat transfer in supersonic compression corner flows

Chuvakhov, P. V.; Radchenko, Vladimir

doi:10.1016/j.ijheatmasstransfer.2020.119310

Cited by 15 publications

(7 citation statements)

References 15 publications

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“…As expected, the most amplified optimal responses and forcings are found to be streamwise streaks and vortices for r c /L = 1.9 and 3.8, respectively (see figure 20). Cossu et al (2000) performed spatial transient growth analysis of an incompressible boundary layer over a concave curved wall and found an optimal response and forcing similar to the present results. For r c /L = 1.9 and 3.8, the most amplified optimal responses occur at βL = 262.3 and 287.5 (λ/L = 0.024 and 0.022), respectively.…”

Section: Corner Roundingsupporting

confidence: 78%

“…Furthermore, a pair of oblique first-mode waves can generate steady streamwise streaks through nonlinear interactions (Lugrin et al 2021), which may become relevant at low supersonic Mach numbers. Here, a recent experiment conducted by Chuvakhov & Radchenko (2020) is considered with the flow conditions given as follows: M ∞ = 8, Re L = 1.77 × 10 5 and T 0 = 735 K. The flow is confirmed to be globally stable by GSA, and the incoming boundary layer only supports the second mode. The wavelength of the streamwise steaks observed from the temperature-sensitive paint image is approximately 3 mm, which agrees well with the present trend.…”

Section: Corner Roundingmentioning

confidence: 99%

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Response of hypersonic compression corner flow to upstream disturbances

2023

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Hypersonic flow over a two-dimensional compression corner is investigated using computational fluid dynamics and global resolvent analysis in this study, which is a continuation of the work done by Hao et al. (J. Fluid Mech., vol. 919, 2021, p. A4). The same baseline free-stream conditions with a Mach number of 7.7 and a unit Reynolds number of 4.2 × 106 m−1 are considered. The ramp angles range from 0° (equivalent to a flat plate) to 12° (slightly below the critical angle of global instability). During this process, the base flow evolves from no separation to incipient separation to large separation. The resolvent analysis reveals that the optimal response to upstream disturbances localised near the leading edge is in the form of steady streamwise streaks for all interaction strengths, which arise from transient growth in the flat-plate boundary layer due to the lift-up mechanism and significantly grow near the corner due to the Görtler instability. The most amplified spanwise wavelength decreases as the ramp angle is increased and scales with the incoming boundary-layer thickness.

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Section: Corner Roundingsupporting

confidence: 78%

Section: Corner Roundingmentioning

confidence: 99%

Response of hypersonic compression corner flow to upstream disturbances

2023

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“…Although three-dimensionality has been observed for compression-ramp flows, the physical mechanism underlying the observed phenomena is only partially understood. The most remarkable phenomenon is the streamwise heat-flux streaks formed on the ramp surface, which has been reported in numerous experimental (Ginoux 1971;Simeonides & Haase 1995;Roghelia et al 2017b;Chuvakhov & Radchenko 2020) and numerical (Ohmichi & Suzuki 2013;Cao, Klioutchnikov & Olivier 2019;Dwivedi et al 2019) studies. Conventionally, the streamwise streaks are attributed to the formation of Görtler vortices supported by the concave flow curvature in the reattaching flow regions (Ginoux 1971;Simeonides & Haase 1995).…”

Section: Introductionmentioning

confidence: 75%

Leading-edge bluntness effects on hypersonic three-dimensional flows over a compression ramp

et al. 2021

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“…A remarkable phenomenon observed in compression-ramp experiments is the formation of streamwise heat-flux streaks on the ramp surface (Simeonides & Haase 1995;Chuvakhov et al 2017;Roghelia et al 2017a,b;Chuvakhov & Radchenko 2020). In addition to the intrinsic instability mentioned previously, convective mechanisms can also lead to the appearance of streamwise streaks.…”

Section: Introductionmentioning

confidence: 93%

“…2017; Roghelia et al. 2017 a , b ; Chuvakhov & Radchenko 2020). In addition to the intrinsic instability mentioned previously, convective mechanisms can also lead to the appearance of streamwise streaks.…”

Section: Introductionmentioning

confidence: 97%

Stability of hypersonic flow over a curved compression ramp

Hao¹,

Guo²,

Wen³

et al. 2023

J. Fluid Mech.

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In this work, the stability of hypersonic flow over a curved compression ramp is studied using several stability analysis tools and direct numerical simulations (DNS). The free-stream Mach number and the unit Reynolds number are 7.7 and $4.2 \times 10^6$ m $^{-1}$ , respectively. Corner rounding is considered to alter the separation bubble flow so as to suppress the intrinsic instability of the compression-ramp flow. The variation of intrinsic instability is confirmed by global stability analysis. Subsequently, resolvent analysis is employed to examine the response of intrinsically stable flows to external disturbances. It is shown that the considered flows strongly amplify low-frequency streamwise streaks with a preferential spanwise wavelength. This result is verified using DNS by introducing a random forcing upstream of the separation point. Furthermore, both resolvent analysis and DNS demonstrate that the separation bubble contributes little to the selection of the spanwise wavelength of streamwise streaks. The combined effects of convective and intrinsic instabilities are also explored using DNS. A better agreement with experimental data is achieved after introducing upstream disturbances in an inherently unstable flow.

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Effect of Görtler-like vortices of various intensity on heat transfer in supersonic compression corner flows

Cited by 15 publications

References 15 publications

Response of hypersonic compression corner flow to upstream disturbances

Response of hypersonic compression corner flow to upstream disturbances

Leading-edge bluntness effects on hypersonic three-dimensional flows over a compression ramp

Stability of hypersonic flow over a curved compression ramp

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