Theoretical Performance of Liquid Hydrogen with Liquid Hydrogen as Rocket Propellant PDF Download
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Author:
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ISBN:
Category : Jet propulsion
Languages : en
Pages : 1
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Author:
Publisher:
ISBN:
Category : Jet propulsion
Languages : en
Pages : 1
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Book Description
![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: H. W. Douglass
Publisher:
ISBN:
Category : Hydrogen as fuel
Languages : en
Pages : 58
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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: Sanford Gordon
Publisher:
ISBN:
Category :
Languages : en
Pages : 28
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Author: Anthony Fortini
Publisher:
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.
Author: Ray Morris Bowen
Publisher:
ISBN:
Category :
Languages : en
Pages : 344
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 60
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Author: John L. Sloop
Publisher:
ISBN:
Category : Hydrogen as fuel
Languages : en
Pages : 350
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Author: William L. Jones
Publisher:
ISBN:
Category : Boron as fuel
Languages : en
Pages : 38
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