Theoretical Performance of Hydrogen-oxygen Rocket Thrust Chambers PDF Download
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Author: Gilbert K. Sievers Publisher: ISBN: Category : Hydrogen oxygen fuel cells Languages : en Pages : 88
Book Description
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.
Author: Gilbert K. Sievers Publisher: ISBN: Category : Hydrogen oxygen fuel cells Languages : en Pages : 88
Book Description
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.
Author: Publisher: ISBN: Category : Jet propulsion Languages : en Pages : 139
Book Description
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.
Author: Rene Nardi Rezende Publisher: SAE International ISBN: 0768095425 Category : Technology & Engineering Languages : en Pages : 158
Book Description
The great engineering achievement required to overcome most of the challenges and obstacles that prevented turning rocket design from art into science took place in Europe and the United States between the 1930s and the 1950s. With the vast majority of the engines currently in operation developed in the “pre-computer” age, there are new opportunities to update the design methodologies using technology that can now handle highly complex calculations fast. The space sector with an intense focus on efficiency is driving the need for updating, adapting or replacing the old modeling practices with new tools capable of reducing the volume of resources and the time required to complete simulations and analysis. This book presents an innovative parametric model applicable to the project of some elements of the liquid rocket thrust chamber with the level of detail and accuracy appropriate to the preliminary design phase. It addresses the operating characteristics and dimensioning of some thrust chamber elements through a set of equations and parameters, which include thrust or propellant characteristics. The model degree of sophistication was adjusted to the requirements of the Project Life Cycle Phase B, while also enabling quick analysis of new configurations from changes in initial project parameters.
Author: Gilbert K. Sievers
Author: Gilbert K. Sievers
Author: UNITED STATES. NATIONAL AERONAUTICS AND SPACE ADMINISTRATION.
Author: Gilbert K. Sievers![Theoretical Performance of Hydrogen-oxygen Rocket Thrust Chambers [with List of References] PDF](https://books.google.com/books/content/images/frontcover/fDufwgEACAAJ?fife=w80-h100)
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Author: Gilbert K. Sievers![Theoretical Performance of Liquid Hydrogen with Liquid Oxygen as Rocket Propellant [with List of References] PDF](https://books.google.com/books/content/images/frontcover/f0ZnGwAACAAJ?fife=w80-h100)
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Author: H. W. Douglass
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Author: Hugh M. Henneberry
Author: Rene Nardi Rezende