Interférence stripping et noyau composé dans la réaction 16O(d, p1) (Ed < 1,2 MeV)

The 16O( p1)17O* (871 keV) angular distributions are analysed by stripping-compound effect calculation near Ed ~ 0.450, 0.650 and 1 MeV resonances reported previously.Les distributions angulaires de la réaction 16O(d, p 1)17O* (871 keV) sont analysées par interférence de stripping (DWBA) et noyau composé autour des résonances à Ed ~ 0,450, 0,650 et 1 MeV mises en évidence dans un travail antérieur

Cowl and cavity effects on mixing and combustion in scramjet engines

To investigate the supersonic combustion patterns in scramjet engines, a model scramjet engine was tested in the T4 free-piston shock tunnel. The test model had a rectangular intake, which compressed the freestream flow through a series of four shock waves upstream of the combustor entrance. A cavity flame holder was installed in the supersonic combustor to improve ignition. The freestream test condition was fixed at Mach 7.6, at an altitude of 31 km. This experimental study investigated the effects of varying fuel equivalence ratios, the influence of the cavity flame holder, and the effects of cowl shape. As a result, supersonic combustion was observed at equivalence ratios between 0.11 and 0.18. Measurements indicated that the engine thermally choked at a fuel equivalence ratio of 0.40. Furthermore, the cavity flame holder and the W-shaped cowl showed improved pressure distribution due to greater reaction intensity. With the aid of numerical analysis, the cavity and the W-shaped cowl are shown to be effective in fuel–air mixing