Theoretical Performance of Liquid Hydrogen with Liquid Oxygen as Rocket Propellant [with List of References] PDF Download
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Author:
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Category : Jet propulsion
Languages : en
Pages : 139
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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.
![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)
Author:
Publisher:
ISBN:
Category : Jet propulsion
Languages : en
Pages : 139
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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: Gilbert K. Sievers
Publisher:
ISBN:
Category : Hydrogen oxygen fuel cells
Languages : en
Pages : 88
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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: H. W. Douglass
Publisher:
ISBN:
Category : Hydrogen as fuel
Languages : en
Pages : 58
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Author: Vearl N. Huff
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ISBN:
Category : Charts, diagrams, etc
Languages : en
Pages : 58
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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.
Author:
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ISBN:
Category : Jet propulsion
Languages : en
Pages : 1
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Author: Sanford Gordon
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 94
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Author: Sanford Gordon
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ISBN:
Category :
Languages : en
Pages : 28
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Author: Vearl N. Huff
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ISBN:
Category : Aeronautics
Languages : en
Pages : 36
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Author: Anthony Fortini
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ISBN:
Category : Charts, diagrams, etc
Languages : en
Pages : 38
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Theoretical rocket performance for frozen and equilibrium composition during expansion was calculated for the propellant combination of liquid hydrogen and liquid fluorine at a chamber pressure of 600 pounds per square inch absolute and several pressure ratios and oxidant-fuel ratios.
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ISBN:
Category :
Languages : en
Pages : 60
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