ISSN Online: 2688-7231
ISBN Online: 978-1-56700-478-6
Proceedings of the 24th National and 2nd International ISHMT-ASTFE Heat and Mass Transfer Conference (IHMTC-2017)
WALL HEAT FLUX COMPUTATION FOR SCRAMJET ENGINE AT MACH 6 FLIGHT CONDITION
Аннотация
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