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Aerothermodynamic effects of controlled heat release within the hypersonic shock layer around a large angle blunt cone

Deep, Sneh and Jagadeesh, G (2018) Aerothermodynamic effects of controlled heat release within the hypersonic shock layer around a large angle blunt cone. In: PHYSICS OF FLUIDS, 30 (10).

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Official URL: http://dx.doi.org/10.1063/1.5046191


Effects of controlled heat addition into the high temperature, chemically reacting shock layer of a large angle (60 degrees) blunt cone with a spherical nose have been experimentally investigated. The exothermic oxidation of ablated chromium from the surface of the cone at hypersonic Mach numbers triggers the heat release process. A conical skirt with a base diameter of 70 mm and a semi-apex angle of 30 degrees, culminating into a nose of radius 30 mm, has been used as the test model. An in-house hypersonic free-piston driven shock tunnel facility, HST3, was used for the experiments at a stagnation enthalpy of 6.31 MJ/kg and a freestream Mach number of 9.84. The temperature distribution in the shock layer was experimentally measured by the two-color ratio pyrometry technique, using a Digital Single Lens Reflex (DSLR) camera as a pyrometer. The temperature field was corrected for discrete radiative line emissions obtained through emission spectroscopy. Surface heat flux measurements were taken using carefully calibrated thin film platinum heat transfer gauges mounted on an insulating Macor substrate. Shock stand-off distances were measured through Schlieren imaging of the flow using a high-speed camera at 20 000 frames per second, and also by a new intensity-scan based method using the processed color image from the DSLR camera. Calculations showed a 173 K rise in the temperature of the gas layer in the stagnation region due to chromium oxidation. The net surface heat flux on the blunt cone was also found to increase by about 31 W/cm(2). The shock stand-off distance, as ascertained from Schlieren images, increased from about 3.82 mm (+/- 1.4%) to 4.45 mm (+/- 1.5%), a 17% rise. Analytical calculations, taking chromium oxidation reaction kinetics into consideration, to relate the total exothermic heat release to its distribution into various processes demonstrated that chromium oxidation releases about 78 W/cm(2) energy in the stagnation region of the shock layer. 1.9% of this energy increases the temperature of the gas layer, 40% is convected back into the airframe, 0.4% is lost from the rear of the Macor substrate by conduction, and about 8% is radiated into the model. The remaining 50% of the heat was used up in pushing the shock layer away from the body by raising its density, thereby increasing shock stand-off distance. Published by AIP Publishing.

Item Type: Journal Article
Additional Information: Copy right for this article belong to AMER INST PHYSICS
Department/Centre: Division of Mechanical Sciences > Aerospace Engineering(Formerly Aeronautical Engineering)
Date Deposited: 22 Nov 2018 15:03
Last Modified: 22 Nov 2018 15:03
URI: http://eprints.iisc.ac.in/id/eprint/61122

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