An Investigation into the Feasibility of Using a Dual-Combustion Mode Ramjet in a High Mach Number Tactical Missile.
Abstract
An investigation into the feasibility of using a solid fuel, dual combustion mode ramjet in a high Mach number tactical missile was conducted to determine the regimes where this propulsion plant might be superior to a conventional solid fuel ramjet. The results of the study show that at Mach 6, 80,000 feet, with a temperature rise combustion efficiency of 90%, the DMRJ performance exceeded that of the SFRJ by 20% at near stoichiometric overall fuel-to-air ratios, neglecting mixing losses in the supersonic combustor. It also appears that eta delta T must be greater than 70% in order for the DMRJ to outperform the conventional SFRJ. Keywords: Ramjet, Scramjet, Dual combustion ramjet, Supersonic combustion, Solid fuel propulsion.
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 1987
- Accession Number
- ADA186906
Entities
People
- Clifford B. Vaught
Organizations
- Naval Postgraduate School