Indian Society for Heat and Mass Transfer

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Prabhu M Ram
Vikram Sarabhai Space Center Thiruvananthapuram, Kerala, India

T. V. Radhakrishnan
Vikram Sarabhai Space Centre, ISRO, Thiruvananthapuram, Kerala, India, 695522

M. J. Chacko
Aerothermal Design and Analysis Division Vikram Sarabhai Space Centre Thiruvananthapuram

DOI: 10.1615/IHMTC-2017.1480
pages 1061-1065


Aerothermal design is a key aspect in design and development of air breathing scramjet engines. Hypersonic vehicles in dense atmospheres experience severe aerodynamic heating at leading edges and intake compression ramps. Combustor duct walls experience high heating owing to reflected shock systems and supersonic combustion. ISRO successfully demonstrated supersonic combustion in flight. Two scramjet engine modules were attached to the aft end of second stage of the carrier vehicle. During the flight, supersonic combustion under regulated fuel supply mode was achieved. Flight thermal measurements provide valuable insight on the heating levels experienced at critical regions. This paper examines the heat flux measurements carried out at intake ramp and combustor regions of the scramjet engine module during flight. Slug type heat flux sensors were instrumented with one at inlet ramp and two heat flux sensors in combustor region for both engines. Heat flux was derived from the measured thermal response of the slug gauge. Thermal model of the slug heat flux sensor was also generated to predict slug temperature history for derived heating rates. The measured aerodynamic heat flux at intake ramp is in good agreement with estimated. The measured heat flux inside combustor duct behind struts shows severe heating levels indicating successful combustion during flight.

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