Accession Number : ADA186906

Title :   An Investigation into the Feasibility of Using a Dual-Combustion Mode Ramjet in a High Mach Number Tactical Missile.

Descriptive Note : Master's thesis,

Corporate Author : NAVAL POSTGRADUATE SCHOOL MONTEREY CA

Personal Author(s) : Vaught, Clifford B

PDF Url : ADA186906

Report Date : Sep 1987

Pagination or Media Count : 84

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.

Descriptors :   *SOLID FUELS, *SUPERSONIC COMBUSTION RAMJET ENGINES, COMBUSTION, COMBUSTORS, FUEL AIR RATIO, FUELS, LOSSES, MIXING, PROPULSION SYSTEMS, RAMJET ENGINES, SOLID PROPELLANTS, SUPERSONIC COMBUSTION, EFFICIENCY, HYPERSONIC FLIGHT, GUIDED MISSILES, THESES

Subject Categories : Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE