Hypersonic shock impingement on a heated flat plate at Mach 7 flight enthalpy

Chang, Eric Won Keun; Chan, W. Y. K.; McIntyre, Timothy J.; Veeraragavan, Ananthanarayanan

doi:10.1017/jfm.2020.877

Cited by 17 publications

(17 citation statements)

References 28 publications

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“…The Reynolds number at this location is 2.16 × 10 6 , consistent with the transition Reynolds number of 2 × 10 6 developed from previous flat plate studies in T4 (Mee 2002). The heat-transfer measurements from both conditions indicate that the boundary layers are laminar upstream of the expected shock impingement locations (x ≈ 260 mm), confirmed in the heated SBLI work (Chang et al 2021).…”

Section: Flow Establishment and Mean Surface Propertiessupporting

confidence: 87%

“…Therefore, this study aims to fill this gap with detailed surface data from an impinging SBLI experiment conducted in the University of Queensland's T4 Stalker Tube. In line with this, the present authors examined the effect of high wall temperatures in impinging shock-induced flow separation on a heated flat plate (Chang et al 2020(Chang et al , 2021. One shortcoming of the hot-wall studies was that the model lacked surface instrumentation due to its high wall temperature.…”

Section: Introductionmentioning

confidence: 94%

“…From the shock impingement studies on a heated plate (Chang et al 2021), we discovered that the effect of wall temperature follows a different scaling than the existing separation length (L sep ) correlations (Katzer 1989;Bleilebens & Olivier 2006):…”

Section: Remarks On the Separation Lengthmentioning

confidence: 99%

“…Above the flat plate, a 215-mm-long, 172-mm-wide shock generator plate was positioned at 12 • and 16 • deflection to the freestream, producing an inviscid shock strength ( p 2 / p ∞ ) of 5.53 and 8.35, respectively. While the 12 • shock generator was positioned at the same location as that of the previous work (Chang et al 2021), the 16 • generator was positioned at x = 40 mm and y = 90 mm to impinge a shock at a similar location as the 12 • shock generator. Theoretical impingement locations of the 12 • and 16 • generators at Mach 7 freestream were x ≈ 260.4 mm and x ≈ 255.1 mm, respectively.…”

Section: Test Models and Data Collectionmentioning

confidence: 99%

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Hypersonic shock impingement studies on a flat plate: flow separation of laminar boundary layers

et al. 2022

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Interactions between shock waves and boundary layers produce flow separations and augmented pressure/thermal loads in hypersonic flight. This study provides details of Mach 7 impinging-shock-flat-plate experiments conducted in the T4 Stalker Tube. Measurements were taken at flow conditions of Mach 7.0 (2.44 MJ kg $^{-1}$ ) and Mach 7.7 (2.88 MJ kg $^{-1}$ ) flight enthalpies with a range of freestream unit Reynolds numbers from $1.43 \times 10^{6}$ m $^{-1}$ to $5.01 \times 10^{6}$ m $^{-1}$ . A shock generator at $12^{\circ }$ or $16^{\circ }$ to the freestream created an oblique shock which impinged on a boundary layer over a flat plate to induce flow separation. The flow field was examined using simultaneous measurements of wall static pressure, heat transfer and schlieren visualisation. Measured heat transfer along the flat plate without the shock impingement indicated that the boundary layer remained laminar for all flow conditions. The shock impingement flow field was successfully established within the facility test duration. The onset of separation was observed by a rise in wall pressure and a decrease in heat transfer at the location corresponding to the stem of the separation shock. Downstream of this initial rise, an increased pressure and higher heating loads were observed. The heat-transfer levels also indicated an immediate boundary layer transition due to the shock impingement. The separation data of the present work showed good agreement with our previous work on shock impingement on heated walls (Chang et al., J. Fluid Mech., vol. 908, 2021, pp. 1–13). A comparison with the previous scaling indicated that the separation also relates to the pressure ratio and the wall temperature parameter.

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Section: Flow Establishment and Mean Surface Propertiessupporting

confidence: 87%

Section: Introductionmentioning

confidence: 94%

Section: Remarks On the Separation Lengthmentioning

confidence: 99%

Section: Test Models and Data Collectionmentioning

confidence: 99%

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Hypersonic shock impingement studies on a flat plate: flow separation of laminar boundary layers

et al. 2022

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“…Another correlation based on Katzer (1989) has recently been used by Chang et al. (2021) for an impinging shock SBLI on a heated flat plate in a Mach 7 high-enthalpy hypersonic flow. They found that the correlation of Bleilebens & Olivier (2006) for a heated compression ramp at hypersonic Mach numbers was not quite applicable to an impinging shock SBLI.…”

Section: Introductionmentioning

confidence: 99%