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WALL HEAT FLUX COMPUTATION FOR SCRAMJET ENGINE AT MACH 6 FLIGHT CONDITION

Amit Singh
Aerodynamics R & D Division

C. Babu
Aerodynamics R & D Division

Dipankar Das
Aerodynamics R & D Division

G Vidya
Aerodynamics R & D Division, Aerodynamics and Aerothermal Group, Vikram Sarabhai Space Centre Thiruvanthapuram, India

V. Ashok
AERO Vikram Sarabhai Space Centre, Thiruvananthapuram, India

DOI: 10.1615/IHMTC-2017.3240
pages 2325-2327

Abstract

This paper describes the numerical study carried out to estimate the scramjet engine heat flux with and without combustion at Mach 6 flight condition. The prediction of heat flux on the ramp surface and combustor wall is quite tricky, due to the complex flow interaction and combustion. Using a commercial software CFD++, full engine simulation are carried out with and without combustion along with cone cylinder fore body. Hydrogen as fuel is injected axially into the incoming free stream through the injection ports located on the struts base at sonic condition. Computational analysis provides a detailed study of both reacting and non reacting supersonic combustor flow field. In this study the heat flux on the ramp, isolator, combustor and the nozzle is computed and it is found that due to combustion heat transfer on the wall increases significantly

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