Mumerical investigation on subdetonative model ramjet-in-tube

摘要

Numerical simulation on a subdetonative mode ramjet-in-tube were made according to the proposed specifications on the flight model geometry and test section for RAMAC III Benchmark Test. They were made also according to others configurations using different model geometries plus small variations in combustible mixture composition and different initial pressures. For the numerical simulation it is supposed that a pre-launcher section pushed the obturator plus projectile combination to a 1.4 km/s, that is the entrance velocity in the ramjet-in-tue combustion section. The combustion was then initiated by the stagnation flow on the obturator before it was discarded by gasdynamic drag. A simplified model based on the one dimensional inviscid flow and equilibrium chemical reaction computation was tested. The various theoretical and experimetnal resutls encountered in the available technical literature were confronted with the numerical modelling developed in the present paper and the resutls correlated well.