Forebody Convective Hypersonic Heat Transfer Measurements over Large-Angle Blunt Cones

Jagadeesh, G.; Reddy, N. M.; Nagashetty, K.; Reddy, K. P. J.

doi:10.2514/2.3537

Cited by 28 publications

(7 citation statements)

References 7 publications

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“…The heat penetration depth is inversely proportional to the square root of the thermal diffusivity and the effective test time. Therefore, for macor, with a thermal diffusivity of 7.94 X 10"''m^/s and test times of 600-1000 ^s the thickness required is around 5 mm [17]. For this set of experiments, the macor thickness was kept at 6 mm.…”

Section: Heat Transfer Measurementmentioning

confidence: 99%

Experimental Investigation of Heat Fluxes in the Vicinity of Protuberances on a Flat Plate at Hypersonic Speeds

Kumar¹,

Reddy

2013

Journal of Heat Transfer

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Heat transfer rates measured in front and to the side of a protrusion on an aluminum flat plate subjected to hypersonic flow at zero angle of attack are presented for two flow enthalpies of approximately 2 M J/kg and 4.5 M J/kg. Experiments were conducted in the hypersonic shock tunnel (HST2) and free piston driven HST3 at a freestream Mach number of 8. Heat transfer data was obtained for different geometries of the protrusion of a height of 4 mm, which is approximately the local boundary layer thickness. Comparatively high rates of heat transfer were obtained at regions of flow circulation in the separated region, with the hottest spot generally appearing in front of the protuberance. Experimental values showed moderate agreement with existing empirical correlations at higher enthalpy but not at all for the lower enthalpy condition, although the correlations were coined at enthalpy values nearer to the lower value. Schlieren visualization was also done to investigate the flow structures qualitatively.

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Section: Heat Transfer Measurementmentioning

confidence: 99%

Experimental Investigation of Heat Fluxes in the Vicinity of Protuberances on a Flat Plate at Hypersonic Speeds

Kumar¹,

Reddy

2013

Journal of Heat Transfer

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“…Scramjet studies have been carried out in HDST2 [137,143]. Available shock-tubes at IIT Bangalore such as HDST1 have been used to establish heating correlations [144] for re-entry applications and for investigating chemical kinetics related to scramjet combustion [145].…”

Section: Indian Shock-tunnelsmentioning

confidence: 99%

Survey of high-enthalpy shock facilities in the perspective of radiation and chemical kinetics investigations

Reynier¹

2016

Progress in Aerospace Sciences

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“…For macor, with a thermal diffusivity 7.94 × 10 −7 m 2 /s and experimental test times of 600-1000 µs, the thickness required is greater than approximately 5 mm. 28 For the current experiments, the thickness was chosen to be 6 mm.…”

Section: Heat Flux Measurementmentioning

confidence: 99%

Investigation of the separated region ahead of three-dimensional protuberances on plates and cones in hypersonic flows with laminar boundary layers

2014

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Heat transfer rate and pressure measurements were made upstream of surface protuberances on a flat plate and a sharp cone subjected to hypersonic flow in a conventional shock tunnel. Heat flux was measured using platinum thin-film sensors deposited on macor substrate and the pressure measurements were made using fast acting piezoelectric sensors. A distinctive hot spot with highest heat flux was obtained near the foot of the protuberance due to heavy vortex activity in the recirculating region. Schlieren flow visualization was used to capture the shock structures and the separation distance ahead of the protrusions was quantitatively measured for varying protuberance heights. A computational analysis was conducted on the flat plate model using commercial computational fluid dynamics software and the obtained trends of heat flux and pressure were compared with the experimental observation. Experiments were also conducted by physically disturbing the laminar boundary layer to check its effect on the magnitude of the hot spot heat flux. In addition to air, argon was also used as test gas so that the Reynolds number can be varied. C 2014 AIP Publishing LLC. [http://dx.

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Forebody Convective Hypersonic Heat Transfer Measurements over Large-Angle Blunt Cones

Cited by 28 publications

References 7 publications

Experimental Investigation of Heat Fluxes in the Vicinity of Protuberances on a Flat Plate at Hypersonic Speeds

Experimental Investigation of Heat Fluxes in the Vicinity of Protuberances on a Flat Plate at Hypersonic Speeds

Survey of high-enthalpy shock facilities in the perspective of radiation and chemical kinetics investigations

Investigation of the separated region ahead of three-dimensional protuberances on plates and cones in hypersonic flows with laminar boundary layers

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