Kumar, CS and Reddy, KPJ (2013) Experimental Investigation of Heat Fluxes in the Vicinity of Protuberances on a Flat Plate at Hypersonic Speeds. In: JOURNAL OF HEAT TRANSFER-TRANSACTIONS OF THE ASME, 135 (12).
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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 MJ/kg and 4.5 MJ/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.
|Item Type:||Journal Article|
|Additional Information:||Copyright for this article belongs to the ASME|
|Keywords:||hypersonic flow; laminar boundary layer; three-dimensional flow interference; flow separation; platinum thin-film gauges|
|Department/Centre:||Division of Mechanical Sciences > Aerospace Engineering (Formerly, Aeronautical Engineering)|
|Date Deposited:||18 Dec 2013 08:38|
|Last Modified:||18 Dec 2013 08:38|
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