The following papers have been accepted but have not been finalized (proof reading) yet.
«« Back

Numerical Study on Shock Train Characteristics in Divergent Channels
Author(s): Vignesh Ram Petha Sethuraman, Tae Ho Kim, Heuy Dong Kim
Keywords: Shock boundary layer interaction, Pseudo shock wave, Separated flows, Shock reflection phenomenon
In any supersonic intake, the flow decelerates from supersonic to subsonic speed through a constant or divergent channel ``isolator" by a series of bifurcated compression shock wave referred as shock train. It is important to understand the characteristics of the shock train occurs inside the isolator to improve the performance of the scramjet engines. In the present work, numerical simulations are carried out to investigate the characteristics of the shock train occurs in the divergent channels using coupled implicit Reynolds Averaged Navier-Stokes (RANS) equations along with the two equation k-w SST turbulence model. Results shows that the downstream pressure variation causes the shock train length to decrease and the shock structure varies Mach reflection to Regular reflection phenomenon. The variation of inlet Mach number has less influence on the shock train length and the location of shock train is determined by the area ratio. In comparison with constant area duct, the shock train structure varies from Mach reflection to regular reflection phenomena in divergent channel. Also the increase in divergent angle increases the total pressure loss.