Download or read book Theoretical Performance of JP 4 Fuel and Liquid Oxygen as a Rocket Propellant written by Vearl N. Huff and published by . This book was released on 1956 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt: Data were calculated for equivalence ratios of 1 to 3, chamber pressures of 300 and 600 pounds per square inch absolute, and pressure ratios of 1 to 1500. Parameters included are specific impulse, combustion and exit temperature, molecular weight, characteristic velocity, coefficient of thrust, ratio of nozzle-exit area to throat area, specific heat at constant pressure, isentropic exponent, viscosity, and thermal conductivity. A correlation is given which permits determination of performance for a wide range of chamber pressure.
Download or read book Rockets Using Liquid Oxygen written by Adolf Busemann and published by BiblioGov. This book was released on 2013-07 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt: It is my task to discuss rocket propulsion using liquid oxygen and my treatment must be highly condensed for the ideas and experiments pertaining to this classic type of rocket are so numerous that one could occupy a whole morning with a detailed presentation. First, with regard to oxygen itself as compared with competing oxygen carriers, it is known that the liquid state of oxygen, in spite of the low boiling point, is more advantageous than the gaseous form of oxygen in pressure tanks, therefore only liquid oxygen need be compared with the oxygen carriers. The advantages of liquid oxygen are absolute purity and unlimited availability at relatively small cost in energy. The disadvantages are those arising from the impossibility of absolute isolation from heat; consequently, allowance must always be made for a certain degree of vaporization and only vented vessels can be used for storage and transportation. This necessity alone eliminates many fields of application, for example, at the front lines. In addition, liquid oxygen has a lower specific weight than other oxygen carriers, therefore many accessories become relatively larger and heavier in the case of an oxygen rocket, for example, the supply tanks and the pumps. The advantages thus become effective only in those cases where definitely scheduled operation and a large ground organization are possible and when the flight requires a great concentration of energy relative to weight. With the aim of brevity, a diagram of an oxygen rocket will be presented and the problem of various component parts that receive particularly thorough investigation in this classic case but which are also often applicable to other rocket types will be referred to.
Download or read book Rockets Using Liquid Oxygen written by Adolf Busemann and published by . This book was released on 1947 with total page 11 pages. Available in PDF, EPUB and Kindle. Book excerpt: It is my task to discuss rocket propulsion using liquid oxygen and my treatment must be highly condensed for the ideas and experiments pertaining to this classic type of rocket are so numerous that one could occupy a whole morning with a detailed presentation.
Download or read book A High performance 250 pound thrust Rocket Engine Utilizing Coaxial flow Injection of JP 4 Fuel and Liquid Oxygen written by Samuel Stein and published by . This book was released on 1959 with total page 18 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Analysis of Rocket powered Ejectors for Pumping Liquid Oxygen and Liquid Hydrogen written by Leo C. Franciscus and published by . This book was released on 1970 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: A preliminary analysis of the use of rocket-powered ejectors for pumping liquid oxygen and liquid hydrogen in rocket engines was made. The drive gas is the exhaust gas of a smaller hydrogen-oxygen rocket engine. The analysis is one-dimensional and does not include shock or friction losses. For a nominal drive rocket chamber pressure of 600 psia (4.14 N/m (to the second power) abs), ideal discharge pressures over 2500 psia (17.25X10 (to the sixth power) N/m (to the second power) abs) for oxygen and 400 psia (2.75x10 (to the sixth power) N/m (to the second power) abs) for hydrogen were calculated. Ejector mass ratios (ratio of oxygen or hydrogen mass flow to drive gas flow) resulting in good performance were on the order of 300 for oxygen and 200 for hydrogen.
Download or read book Effect of Fuel Drop Size and Injector Configuration on Screaming in a 200 pound thrust Rocket Engine Using Liquid Oxygen and Heptane written by Charles E. Feiler and published by . This book was released on 1958 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Theoretical Performance of Liquid Ammonia with Liquid Oxygen as a Rocket Propellant written by Sanford Gordon and published by . This book was released on 1958 with total page 94 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Modern Engineering for Design of Liquid Propellant Rocket Engines written by Dieter K. Huzel and published by AIAA. This book was released on 1992 with total page 452 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Theoretical Performance of Liquid Hydrogen with Liquid Oxygen as Rocket Propellant with List of References written by and published by . This book was released on 1959 with total page 139 pages. Available in PDF, EPUB and Kindle. Book excerpt: Theoretical rocket performance for both equilibrium and frozen composition during expansion was calculated for the propellant combination liquid hydrogen and liquid oxygen at four chamber pressures (60, 150, 300, and 600 lb/sq in. abs) and a wide range of pressure ratios (1 to 4000) and oxidant-fuel ratios (1.190 to 39.683). Data are given to estimate performance parameters at chamber pressures other than those for which data are tabulated. The parameters included are specific impulse, specific impulse in vacuum, combustion-chamber temperature, nozzle-exit temperature, molecular weight, molecular-weight derivatives, characteristic velocity, coefficient of thrust, ratio of nozzle-exit area to throat area, specific heat at constant pressure, isentropic exponent, viscosity, thermal conductivity, Mach number, and equilibrium gas compositions.
Download or read book Theoretical Performance of Hydrogen oxygen Rocket Thrust Chambers written by Gilbert K. Sievers and published by . This book was released on 1961 with total page 88 pages. Available in PDF, EPUB and Kindle. Book excerpt: Theoretical rocket performance data for the propellant combination of liquid hydrogen and liquid oxygen are presented in convenient graphical forms to permit rapid determination of specific impulse, vacuum specific impulse, and characteristic velocity. Data are presented for both frozen and equilibrium composition during expansion for chamber pressures of 15, 30, 60, 150, 300, 600, 900 and 1200 pounds per square inch absolute over a wide range of percent fuel from approximately 8 to 34 and area ratios to approximately 300. For rapid calculation of the theoretical nozzle performance with over- or under- expansion, separated flow, and introduction of propellants at different initial conditions or heat loss from the combustion chamber, the following theoretical data are also presented: combustion-chamber temperature, nozzle-exit temperature, and the ratio of chamber-pressure to nozzle-exit pressure. An easy method is given for estimating theoretical specific impulse at chamber pressures other than those presented.
Download or read book Ignition written by John Drury Clark and published by Rutgers University Press. This book was released on 2018-05-23 with total page 288 pages. Available in PDF, EPUB and Kindle. Book excerpt: A classic work in the history of science, and described as “a good book on rocket stuff...that’s a really fun one” by SpaceX founder Elon Musk, readers will want to get their hands on this influential classic, available for the first time in decades. This newly reissued debut book in the Rutgers University Press Classics imprint is the story of the search for a rocket propellant which could be trusted to take man into space. This search was a hazardous enterprise carried out by rival labs who worked against the known laws of nature, with no guarantee of success or safety. Acclaimed scientist and sci-fi author John Drury Clark writes with irreverent and eyewitness immediacy about the development of the explosive fuels strong enough to negate the relentless restraints of gravity. The resulting volume is as much a memoir as a work of history, sharing a behind-the-scenes view of an enterprise which eventually took men to the moon, missiles to the planets, and satellites to outer space.
Download or read book Relations of Combustion Dead Time to Engine Variables for a 20 000 pound thrust Gaseous hydrogen written by Daniel I. Drain and published by . This book was released on 1961 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: Experiments were conducted on an uncooled 20,000lb-thrust gaseous-H and LOX rocket engine over a range of chamber pressure from 45 to 300 psia and oxidant-fuel ratio from 2 to 7. Combustion dead times were measured and compared with dead times calculated from frequency data for two assumed combustion models. Measured combustion dead time decreased with increasing chamber pressure at constant oxidant-fuel ratio or LOX injection velocity. This dead time also decreased with oxidant-fuel ratio at constant chamber pressure or O injection velocity. For the engine model where combustion dead time was considered to be the inverse of twice the measured chamberpressure frequency, only a fair agreement with the measured dead time was obtained. When the measured chamber-pressure frequencies were corrected for gas-dynamics effects in terms of the gas residence time, close agreement with the measured dead times was obtained. (Author).
Download or read book Liquid Rocket and Propellants written by L.E. Bollinger and published by Elsevier. This book was released on 2013-04-22 with total page 699 pages. Available in PDF, EPUB and Kindle. Book excerpt: Liquid Rocket and Propellants
Download or read book Propellant Vaporization as a Criterion for Rocket engine Design written by Marcus F. Heidmann and published by . This book was released on 1959 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Analysis of Chugging in Liquid bipropellant Rocket Engines Using Propellants with Different Vaporization Rates written by Leon M. Wenzel and published by . This book was released on 1965 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Experimental Performance of Liquid Hydrogen and Liquid Fluorine in Regeneratively Cooled Rocket Engines written by H. W. Douglass and published by . This book was released on 1959 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Gaseous hydrogen liquid oxygen Rocket Combustion at Supercritical Chamber Pressures written by Martin Hersch and published by . This book was released on 1967 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
