  The strut based injector has been found to be one of the most promising
injector designs for supersonic combustor, offering en-hanced mixing of fuel
and air. The mixing and flow field characteristics of the straight (SS) &
tapered strut (TS), with fixed ramp an-gle and height at freestream Mach number
2 in conjunction with fuel injection at Mach 2.3 have been investigated
numerically and reported. In the present investigation, hydrogen (H2) and
ethylene (C2H4) are injected in oncoming supersonic flow from the back of the
strut, where jet to freestream momentum ratio is maintained at 0.79 and 0.69
for H2 & C2H4, respectively. The predicted wall static pressure and species
mole fractions at various downstream locations are compared with the
experimental data for TS case with 0.6 mm jet diameter and found to be in good
agreement. Further, the effect of jet diameter and strut geometry on the near
field mixing in strut ramp configuration is discussed for both the fuel. The
numerical results are assessed based on various parameters for the performance
evaluation of different strut ramp configurations. The SS configuration for
both the injectant is found to be an optimum candidate, also it is observed
that for higher jet diameter larger combustor length is required to achieve
satisfactory near field mixing.
