Ram-rocket propulsion system with subsonic combustion

Includes bibliographical references (pages 62-65)This project analyzes the performance of the\ud ram-rocket with subsonic combustion in terms of\ud propellant-air ratio, flight Mach number and altitude.\ud The theoretical analysis of the four basic\ud components: supersonic diffuser, primary combustor,\ud secondary combustor, and exhaust nozzle of the\ud ram-rocket are presented. Because of the complexity of\ud the evaluation of the propellant performance, a trial\ud and error technique is used in a digital computer in\ud order to calculate the desired proerties and performance\ud parameters. A computer code has been developed for this\ud project with a variance of 1) flight Mach number, 3 < M\ud < 5, 2) flight altitude, 15,000 ft < z < 35,000 ft and\ud with a constant area subsonic combustor. This project\ud also provides the effect of the parameters on the\ud propulsion performance characteristics. It shows that:\ud 1) With a constant-area combustor, maximum\ud specific thrust is achieved when sufficient\ud heat is added to choke the flow at the\ud combustor exit.\ud 2) For the same amount of propellant-air ratio the\ud "fuel richer" solid propellant mixture has\ud higher performance in the specific thrust and\ud propellant specific impulse.\ud 3) At the same flight altitude, the thrust and\ud propellant specific impulse increase as the\ud flight Hach number increases.\ud 4) For the same flight Mach number, the higher the\ud flight altitude, the lower the total thrust,\ud propellant specific impulse and thrust power.\ud The ram-rocket seems to be well adapted for\ud reusable boosters, tactical missiles and air to space\ud shuttle vehicles for the present and near future