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An Experimental Investigation of Mass Transfer Cooling Techniques for Atmospheric Entry Vehicles

Mohammed Ibrahim, S and Reddy, KPJ (2020) An Experimental Investigation of Mass Transfer Cooling Techniques for Atmospheric Entry Vehicles. [Book Chapter]

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Official URL: https://doi.org/10.1007/978-981-13-9012-8_3


An experimental campaign was carried out to investigate the feasibility of using mass transfer cooling techniques such as thermal protection system (TPS) for Martian entry spacecraft’s configurations. The tests were performed using hypersonic shock tunnels HST2 and HST3, at Laboratory for Hypersonic and Shock Wave Research (LHSR), IISc, Bangalore, simulating low (1.5 km/s) and high enthalpy (2.5 km/s) flow conditions, respectively. A large angle (60° apex angle) blunt sphere-cone configuration was used as test model, and heat transfer rate to the model surface was measured using platinum thin film sensors. Film and transpiration cooling were the two techniques investigated using nitrogen and helium gas as coolants. The investigations showed that these techniques resulted in reduction in heat transfer, and it was more effective for the high enthalpy test case.

Item Type: Book Chapter
Publication: Green Energy and Technology
Publisher: Springer Verlag
Additional Information: The copyright for this article belongs to Springer Verlag.
Keywords: Cooling; Enthalpy; Hypersonic vehicles; Shock waves, Atmospheric entry; Experimental campaign; Experimental investigations; Heat transfer rate; High-enthalpy test; Platinum thin film; Thermal Protection System; Transpiration cooling, Mass transfer
Department/Centre: Division of Mechanical Sciences > Aerospace Engineering(Formerly Aeronautical Engineering)
Date Deposited: 08 Feb 2023 11:25
Last Modified: 08 Feb 2023 11:25
URI: https://eprints.iisc.ac.in/id/eprint/80089

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