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Analysis of rocket, ram-jet, and turbojet engines for supersonic propulsion of long-range missiles 1: rocket-engine performance

Description: Report presenting theoretical performance characteristics and estimates of effective specific impulse and weight for rocket engines serving a main and booster power plants for missiles. The fuels used included ammonia-fluorine and JP4-oxygen propellants. At extremely high altitudes, the specific impulse depends primarily on the expansion ratio.
Date: July 9, 1954
Creator: Huff, Vearl N. & Kerrebrock, Jack
Partner: UNT Libraries Government Documents Department

Theoretical performance of liquid hydrogen and liquid fluorine as a rocket propellant for a chamber pressure of 600 pounds per square inch absolute

Description: Report presenting theoretical rocket performance for frozen and equilibrium composition during expansion 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. The parameters included were specific impulse, combustion-chamber temperature, nozzle-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.
Date: January 25, 1957
Creator: Fortini, Anthony & Huff, Vearl N.
Partner: UNT Libraries Government Documents Department

Theoretical performance of lithium and fluorine as a rocket propellant

Description: Theoretical performance for liquid lithium and liquid fluorine as a rocket propellant was calculated with assumptions both of equilibrium and frozen composition during expansion. Parameters included were specific impulse, combustion-chamber temperature, nozzle-exit temperature, composition, mean molecular weight, characteristic velocity, coefficient of thrust, and ratio of nozzle-exit area to throat area. For chamber pressure of 300 pounds per square inch absolute and expansion to 1 atmosphere, the maximum equilibrium specific impulse calculated was 335.5 pound-seconds per pound. The effect of ionization on calculated performance was shown to be negligible by comparison of values of various parameters calculated both with and without ionized products of combustion.
Date: May 10, 1951
Creator: Gordon, Sanford & Huff, Vearl N.
Partner: UNT Libraries Government Documents Department

Theoretical performance of mixtures of liquid ammonia and hydrazine as fuel with liquid fluorine as oxidant for rocket engines

Description: Report presenting theoretical values of rocket performance parameters for two mixtures of liquid ammonia and hydrazine as fuels with liquid fluorine as oxidant. The parameters included were specific impulse, combustion-chamber temperature, nozzle-exit temperature, equilibrium composition, mean molecular weight, characteristic velocity, coefficient of thrust, ratio of nozzle-exit area to throat area, specific heat at constant pressure, coefficient of viscosity, and coefficient of thermal conductivity.
Date: July 29, 1953
Creator: Gordon, Sanford & Huff, Vearl N.
Partner: UNT Libraries Government Documents Department

General method for computation of equilibrium composition and temperature of chemical reactions

Description: Report presenting an approximation process that can be used to determine both composition and temperature resulting from a chemical reaction. It is suitable for use with any set of reactants over the complete range of mixture ratios as long as the products of reaction are ideal gases.
Date: June 1950
Creator: Huff, Vearl N. & Morrell, Virginia E.
Partner: UNT Libraries Government Documents Department

Tables of thermodynamic functions for analysis of aircraft-propulsion systems

Description: Report presenting tables of thermodynamic functions for 42 substances containing argon, aluminum, boron, carbon, chlorine, fluorine, hydrogen, lithium, nitrogen, and oxygen. The functions examined included the specific heat at constant pressure, sensible enthalpy, sum of sensible enthalpy and chemical energy, molar entropy, enthalpy change due to formation of substance from elements in atomic gas state divided by gas constant times temperature, and the logarithm of the equilibrium constant at designated temperatures.
Date: August 1950
Creator: Huff, Vearl N. & Gordon, Sanford
Partner: UNT Libraries Government Documents Department

Theoretical performance of JP-4 fuel with a 70-30 mixture of fluorine and oxygen as a rocket propellant 2: Equilibrium composition

Description: Data were calculated for equivalence ratios of 1 to 4, 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 temperatures, 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 pressures. A method for obtaining specific impulse of JP-4 fuel with OF2 and O3-F2 mixtures is given.
Date: October 2, 1956
Creator: Gordon, Sanford & Huff, Vearl N.
Partner: UNT Libraries Government Documents Department

Theoretical performance of JP-4 fuel and liquid oxygen as a rocket propellant 1: frozen composition

Description: Report presenting the theoretical rocket performance for frozen composition during expansion using JP-4 fuel and liquid oxygen at two chamber pressures and several pressure ratios and oxidant-fuel ratios. The parameters included specific impulse, combustion-chamber temperature, nozzle-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.
Date: April 17, 1956
Creator: Huff, Vearl N. & Fortini, Anthony
Partner: UNT Libraries Government Documents Department

Theoretical rocket performance of JP-4 fuel with mixtures of liquid ozone and fluorine

Description: Data were estimated by means of a heat correction equation using data for JP-4 fuel with mixtures of oxygen and flourine. The estimated data were checked for several cases by direct calculations. The difference in specific impulse between the estimated and directly calculated values was from 0.2 to 0.8 pound-second per pound. The maximum value of specific impulse was 334.9 pound-seconds per pound for a combustion-chamber pressure of 600 pounds per square inch absolute and an exit pressure of 1 atmosphere.
Date: January 28, 1957
Creator: Huff, Vearl N. & Gordon, Sanford
Partner: UNT Libraries Government Documents Department

Analysis of Rocket, Ram-Jet, and Turbojet Engines for Supersonic Propulsion of Long-Range Missiles 2 - Rocket Missile Performance

Description: From Summary: "The theoretical performance of a two-stage ballistic rocket missile having a centerbody and two parallel boosters was investigated for J oxygen and ammonia-fluorine propellants. Both power-plant and missile parameters were optimized to give minimum cost on-the basis of the analysis for a range of 5500 nautical miles. After optimum values were found, each parameter was varied independently to determine its effect on performance of the missile."
Date: September 29, 1954
Creator: Huff, Vearl N. & Kerrebrock, Jack
Partner: UNT Libraries Government Documents Department

Theoretical performance of liquid hydrogen and liquid fluorine as a rocket propellant

Description: Theoretical values of performance parameters for liquid hydrogen and liquid fluorine as a rocket propellant were calculated on the assumption of equilibrium composition during the expansion process for a wide range of fuel-oxidant and expansion ratios. The parameters included were specific impulse, combustion-chamber temperature, nozzle-exit temperature, equilibrium composition, mean molecular weight, characteristic velocity, coefficient of thrust, ration of nozzle-exit area to throat area, specific heat at constant pressure, coefficient of viscosity, and coefficient of thermal conductivity. The maximum value of specific impulse was 364.6 pound-seconds per pound for a chamber pressure of 300 pounds per square inch absolute (20.41 atm) and an exit pressure of 1 atmosphere.
Date: February 6, 1953
Creator: Gordon, Sanford & Huff, Vearl N.
Partner: UNT Libraries Government Documents Department

Theoretical performance of liquid ammonia, hydrazine and mixture of liquid ammonia and hydrazine as fuels with liquid oxygen biflouride as oxidant for rocket engines 1: mixture of liquid ammonia and hydrazine

Description: Theoretical performance for mixture of 36.3 percent liquid ammonia and 63.7 percent hydrazine with liquid oxygen bifluoride as rocket propellant was calculated on assumption of equilibrium composition during expansion for a wide range of fuel-oxidant and expansios ratios. Parameters included were specific impulse, combustion-chamber temperature, nozzle exit temperature, composition mean molecular weight, characteristic velocity, coefficient of thrust and ratio of nozzle-exit area to throat area. For chamber pressure of 300 pounds per square inch absolute and expansion to 1 atmosphere, maximum specific impulse was 295.8 pound-seconds per pound. Five percent by weight of water in the hydrazine lowered specific impulse from about one to three units over a wide range of weight-percent fuel.
Date: February 20, 1952
Creator: Huff, Vearl N. & Gordon, Sanford
Partner: UNT Libraries Government Documents Department

Theoretical performance of liquid ammonia and liquid fluorine as a rocket propellant

Description: From Summary: "Theoretical values of performance parameters for liquid ammonia and liquid fluorine as a rocket propellant were calculated on the assumption of equilibrium composition during the expansion process for a wide range of fuel-oxidant and expansion ratios. The parameters included were specific impulse, combustion-chamber temperature, nozzle-exit temperature, equilibrium composition, mean molecular weight, characteristic velocity, coefficient of thrust, ratio of nozzle-exit area to throat area, specific heat at constant pressure, coefficient of viscosity, and coefficient of thermal conductivity."
Date: July 3, 1953
Creator: Gordon, Sanford & Huff, Vearl N.
Partner: UNT Libraries Government Documents Department

Theoretical performance of liquid hydrazine and liquid fluorine as a rocket propellant

Description: From Summary: "Theoretical values of performance parameters for liquid ammonia and liquid fluorine as a rocket propellant were calculated on the assumption of equilibrium composition during the expansion process for a wide range of fuel-oxidant and expansion ratios. The parameters included were specific impulse, combustion-chamber temperature, nozzle-exit temperature, equilibrium composition, mean molecular weight, characteristic velocity, coefficient of thrust, ratio of nozzle-exit area to throat area, specific heat at constant pressure, coefficient of viscosity, and coefficient of thermal conductivity."
Date: July 3, 1953
Creator: Gordon, Sanford & Huff, Vearl N.
Partner: UNT Libraries Government Documents Department

Theoretical performance of mixtures of liquid ammonia and hydrazine as fuel with liquid fluorine as oxidant for rocket engines

Description: Report presenting theoretical values of rocket performance parameters for two mixtures of liquid ammonia and hydrazine with flourine as oxidant for a variety of parameters. Parameters included are specific impulse, combustion chamber temperature, nozzle-exit temperature, equilibrium composition, mean molecular weight, characteristic velocity, coefficient of thrust, ratio of nozzle-exit area to throat area, specific heat at constant pressure, coefficient of viscosity, and coefficient of thermal conductivity.
Date: July 29, 1953
Creator: Gordon, Sanford & Huff, Vearl N.
Partner: UNT Libraries Government Documents Department

Theoretical performance of liquid hydrogen and liquid fluorine as a rocket propellant

Description: Report of theoretical values of performance parameters for liquid hydrogen and flourine as a rocket propellant for a wide range of fuel-oxidant and expansion ratios. Parameters computed include specific impulse, combustion-chamber temperature, nozzle-exit temperature, equilibrium composition, mean molecular weight, characteristic velocity, coefficient of thrust, ratio of nozzle-exit area to throat area, specific heat at constant pressure, coefficient of viscosity, and coefficient of thermal conductivity.
Date: February 6, 1953
Creator: Gordon, Sanford & Huff, Vearl N.
Partner: UNT Libraries Government Documents Department

Analysis of Rocket, Ramjet, Turbojet Engines for Supersonic Propulsion of Long-Range Missiles 2: Rocket Missile Performance

Description: Memorandum presenting an investigation of the theoretical performance of a two-stage ballistic rocket missile with a centerbody and two parallel boosters for JP4-oxygen and ammonia-fluorine propellants. The missile using the ammonia-fluorine propellant weighs about one-half as much as a missile using JP4-oxygen. Results regarding the optimum missile and effect of variation of design parameters are provided.
Date: October 11, 1954
Creator: Huff, Vearl N. & Kerrebrock, Jack
Partner: UNT Libraries Government Documents Department

Charts for the Computation of Equilibrium Composition of Chemical Reactions in the Carbon-Hydrogen-Oxygen-Nitrogen System at Temperatures From 2000 to 5000 K

Description: "A rapidly convergent method is described for the calculation of the equilibrium composition of the carbon-hydrogen-oxygen-nitrogen system in the temperature range from 2000 degrees to 5000 degrees K. Charts are provided for the estimation and progressive adjustment of two independent variables on which the calculations are based. Additional charts are provided for the graphical calculation of the composition. The use of the method and the charts is illustrated by example" (p. 1).
Date: July 1948
Creator: Huff, Vearl N. & Calvert, Clyde S.
Partner: UNT Libraries Government Documents Department

Charts for the Computation of Equilibrium Composition of Chemical Reactions in the Carbon-Hydrogen-Nitrogen System at Temperatures from 2000 to 5000 Degrees K

Description: Charts are provided for the estimation and progressive adjustment of two independent variables on which the calculations are based. Additional charts are provided for the graphical calculation of the composition.
Date: July 1948
Creator: Huff, Vearl N. & Calvert, Clyde S.
Partner: UNT Libraries Government Documents Department

General method and thermodynamic tables for computation of equilibrium composition and temperature of chemical reactions

Description: From Summary: "A rapidly convergent successive approximation process is described that simultaneously determines both composition and temperature resulting from a chemical reaction. This method is suitable for use with any set of reactants over the complete range of mixture ratios as long as the products of reaction are ideal gases. An approximate treatment of limited amounts of liquids and solids is also included. This method is particularly suited to problems having a large number of products of reaction and to problems that require determination of such properties as specific heat or velocity of sound of a dissociating mixture."
Date: January 26, 1950
Creator: Huff, Vearl N.; Gordon, Sanford & Morrell, Virginia E.
Partner: UNT Libraries Government Documents Department

A Mach 4 rocket-powered supersonic tunnel using ammonia-oxygen as working fluid

Description: From Summary: "A rocket-powered supersonic tunnel has been constructed to simulate the high heating rates encountered in hypersonic flow. A gas temperature of 4500 degrees Rankine at Mach 4 has been produced in the 15-inch test section of the tunnel. The calibration pressure data indicate reproducibility of test conditions in this facility. Physical, transport, and one-dimensional aerodynamic data from combustion products of ammonia and oxygen are included."
Date: September 1958
Creator: Graham, Robert W.; Guentert, Eleanor Costilow & Huff, Vearl N.
Partner: UNT Libraries Government Documents Department

Theoretical performance of JP-4 fuel and liquid oxygen as a rocket propellant 2: equilibrium composition

Description: 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 pressures.
Date: September 7, 1956
Creator: Huff, Vearl N.; Fortini, Anthony & Gordon, Sanford
Partner: UNT Libraries Government Documents Department