Fuel Diffusion Immediately behind a Finite-Width Wedge within Supersonic Boundary Layer

Second Report : Effect of Double Wedge

Abstract

The aerodynamic instability induced by a low-height streamwise-symmetrical wedge named Double-Wedge installed on combustor wall was adopted for the passage height recovery of SCRAM jet fuel being attached to the wall. It was attempted that the three-dimensional complicated flow induced around sidewall of the wedge raises the fuel tube toward supersonic airstream, immediately behind the wedge the mixing state of fuel was experimentally confirmed and the flow structure in the wake was numerically clarified. A pair of vertically aligned counter-rotating streamwise vortices was formed and withdrew horizontally a branch part from the main fuel tube. The branch part of fuel holding a firm connection to the main tube extended into main-airstream and achieved successfully the continuous fuel transport from boundary layer to supersonic airstream. In addition, the double-wedge showed superiority to the single-wedge in the aspect of reduction in total-pressure loss.