Aerodynamic Heating Characteristics Over a Protuberance in Hypersonic Flows Using Fast Response Thermo Gauges

Lee, Hyoung Jin; Lee, Bok Jin; Jeung, In‐Seuck; Kim, Seoung-Lyoung; Kim, Insun

doi:10.5139/ijass.2010.11.3.193

Cited by 7 publications

(2 citation statements)

References 9 publications

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“…Lee et al have made attempts to measure heat transfer rates on the protrusion surface using co-axial thermocouples and temperature sensitive paints [9,10]. Since the protrusions themselves can be shielded properly with heat resistant materials, it might be more essential to have a clear understanding of the magnitude of heat flux and location of hot spots in ' [11,12].…”

Section: Introductionmentioning

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: Introductionmentioning

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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“…The focus of this work is on the latter. Lee et al 16,17 employed hypersonic wind tunnel as well as shock tunnel to capture the heat flux distribution on the surface of an attached protuberance on a flat plate. Fast response thermocouples were used in the shock tunnel and temperature sensitive paint in the wind tunnel for acquiring the data, both working at a freestream Mach number of 7.…”

Section: Introductionmentioning

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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Experimental Investigation of Aerodynamic Interference Heat Transfer Around a Protuberance on a Flat Plate Subjected to Hypersonic Flow

Kumar

Reddy

2012

28th International Symposium on Shock Waves

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Aerodynamic Heating Characteristics Over a Protuberance in Hypersonic Flows Using Fast Response Thermo Gauges

Cited by 7 publications

References 9 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

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

Experimental Investigation of Aerodynamic Interference Heat Transfer Around a Protuberance on a Flat Plate Subjected to Hypersonic Flow

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