2019
DOI: 10.1017/jfm.2019.614
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Numerical study of bluntness effects on laminar leading edge separation in hypersonic flow

Abstract: Bluntness effects on laminar hypersonic leading edge separation are investigated numerically at Mach number $M\approx 10$, unit Reynolds number $Re=1.3\times 10^{6}~\text{m}^{-1}$, specific enthalpy $h_{o}=3.1~\text{MJ}~\text{kg}^{-1}$ and wall-to-stagnation temperature ratio $T_{w}/T_{o}=0.1$. Such effects are important from an experimental point of view and because bluntness can affect a separated flow favourably or adversely. In this study, two blunt leading edge cases of small radius ($15~\unicode[STIX]{x0… Show more

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Cited by 8 publications
(17 citation statements)
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“…Khraibut et al. (2019), in particular, showed that for ‘small’ bluntness (as defined later), the results were opposite to those found by Holden (1971). In another recent paper, Chuvakhov et al.…”
Section: Introductionmentioning
confidence: 78%
See 2 more Smart Citations
“…Khraibut et al. (2019), in particular, showed that for ‘small’ bluntness (as defined later), the results were opposite to those found by Holden (1971). In another recent paper, Chuvakhov et al.…”
Section: Introductionmentioning
confidence: 78%
“…(1961), Holden (1971), Stollery (1972), and in recent years, Mason & Lee (1994), Smith & Khorrami (1994), Mallinson, Gai & Mudford (1996), Marini (1998), Borovoy, Skuratov & Struminskaya (2008), Borovoy et al. (2014), John & Kulkarni (2014), Khraibut, Gai & Neely (2019) and Mallinson, Mudford & Gai (2020).…”
Section: Introductionmentioning
confidence: 99%
See 1 more Smart Citation
“…In describing the distinctive flow structure within the wake flow as illustrated in figure 7, the boundary layer separates near the shoulder and a shear layer emanates (Khraibut, Gai & Neely 2019). The flow is first turned as it passes over the shoulder of the capsule resulting in an expansion fan, which curves the bow shock.…”
Section: Line Of Sight Approachmentioning
confidence: 99%
“…Chuvakhov et al (2017) found that both the maximum Stanton numbers in the reattachment region and the amplitude of spanwise oscillations of the Stanton number induced by Görtler-like vortices decreased significantly with small leading-edge bluntness. Recently, Khraibut, Gai & Neely (2019) investigated the effect of bluntness on hypersonic laminar leading-edge separation and found that a large nose radius increased the size of the separation region.…”
Section: Introductionmentioning
confidence: 99%