Numerical Simulation of Fuel Injection for Application to Mach 10-12 Missile

Design of a Shock-Induced Combustion Experiment in an Axisymmetric Configuration with Hydrogen Injection

“…Among the authors who studied the effect of différent injection orifice shapes [13,14,15] and différent momentum flux ratios on the fuel pénétration height and mixing, the work of Hirano et al [16] constitutes a récent and complète summary. They considered several injector geometries, as shown in Figure 2.1: circular, rectangular, wedge-shape, combined circular-wedge-shape, diamond-shape, arrowhead-shape and stinger-shape.…”

“…"OH = l "H 2 = l "H = 0 "H 2 O = 0 (2)(3)(4)(5)(6)(7)(8)(9)(10)(11)(12)(13)(14)(15)(16)(17)(18) Applying Equation (2.16) to this example:…”

“…This means that the allowed time for mixing is much larger than the ignition delay and thus, the combustion is only controlled by the mixing efficiency. This is the reason that motivated research on mixing enhancement in scramjet combustors [13,14,19,30].…”

“…The pénétration height définition is somewhat arbitrary, since it is defined by a pre-determined hydrogen concentration threshold. Some authors [14] chose this threshold to be a hydrogen mass fraction of 0,5%, which is équivalent to a local équivalence ratio of 0,17. Other authors [19] chose a hydrogen mole fraction of 5%, giving 4> = 0,12.…”