Freejet Experimental Investigation on Performance of Dual-Combustion Ramjet

摘要

The performance of dual-combustion ramjet has been investigated through a freejet ground test facility experimentally. The DCR is characterized by the cavity and fuel injected into the supersonic combustor, which deviates from the original concept proposed in [3]. Results show the following: 1) The flow in the inlet of the supersonic combustor is subsonic at Mach 4 but remains supersonic at Mach 6, as is implied by the pressure distribution. 2) The thrust is large enough for the requirements of accelerating at Mach 4 and cruising at Mach 6 of the missile powered by the DCR. But, it is uncertain whether the missile can cruise at Mach 6.5. 3) The DCR shows good performance. When φ ＞ is 1.0 and α is 0 deg, the specific impulse is 11.0, 8.6, and 8.0 kN • s/kg, for Mach 4, 6, and 6.5, respectively. 4) The DCR could work under a wide range of conditions: Mach number from 4 to 6.5, attack angle from 0 to 6 deg (4 deg at Mach 4), and equivalence ratio from 0.78 to 1.0. Thus, the DCR proposed in this Note is a potentially robust and practical one, and it is worth investigating in a further plan.