Author: Sanford Gordon
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 94
Book Description
Theoretical Performance of Liquid Ammonia with Liquid Oxygen as a Rocket Propellant
Author: Sanford Gordon
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 94
Book Description
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 94
Book Description
Theoretical Performance of Liquid Ammonia with Liquid Oxygen as a Rocket Propellant
Author: Sanford Gordon
Publisher:
ISBN:
Category : Charts, diagrams, etc
Languages : en
Pages : 84
Book Description
Theoretical rocket performance for both equilibrium and frozen composition during expansion was calculated for propellant combination liquid ammonia with liquid oxygen at two chamber pressures (300 and 600 lb/sq. in. absolute) and a wide range of pressure ratios (1 to 1500) and oxidant-fuel ratios (0.564 to 7.046).
Publisher:
ISBN:
Category : Charts, diagrams, etc
Languages : en
Pages : 84
Book Description
Theoretical rocket performance for both equilibrium and frozen composition during expansion was calculated for propellant combination liquid ammonia with liquid oxygen at two chamber pressures (300 and 600 lb/sq. in. absolute) and a wide range of pressure ratios (1 to 1500) and oxidant-fuel ratios (0.564 to 7.046).
Theoretical Performance of Liquid Ammonia, Hydrazine and Mixture of Liquid Ammonia and Hydrazine as Fuels with Liquid Oxygen Bifluoride as Oxidant for Rocket Engines
Author: Vearl N. Huff
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 22
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 22
Book Description
Theoretical Performance of Liquid Ammonia, Hydrazine and Mixture of Liquid Ammonia and Hydrazine as Fuels with Liquid Oxygen Bifluoride as Oxidant for Rocket Engines
Author: Vearl N. Huff
Publisher:
ISBN:
Category :
Languages : en
Pages : 24
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 24
Book Description
Theoretical Performance of Liquid Ammonia and Liquid Fluorine as Rocket Propellant
Author: Sanford Gordon
Publisher:
ISBN:
Category :
Languages : en
Pages : 25
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 25
Book Description
Theoretical Performance of Liquid Hydrogen with Liquid Oxygen as Rocket Propellant [with List of References]
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.
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.
Theoretical Performance of Hydrogen-oxygen Rocket Thrust Chambers
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.
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.
Research Memorandum
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 20
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 20
Book Description
Determination of Local Experimental Heat-transfer Coefficients on Combustion Side of an Ammonia-oxygen Rocket
Author: Curt H. Liebert
Publisher:
ISBN:
Category :
Languages : en
Pages : 22
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 22
Book Description
Theoretical Performance of Diborane as a Rocket Fuel
Author: Vearl N. Huff
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 36
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 36
Book Description