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  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
Theoretical method for solution of aerodynamic forces on thin wings in nonuniform supersonic stream with an application to tail surfaces

Theoretical method for solution of aerodynamic forces on thin wings in nonuniform supersonic stream with an application to tail surfaces

Date: November 1, 1948
Creator: Mirels, Harold
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A theoretical method of analyzing the effects of yaw-damper dynamics on the stability of an aircraft equipped with a second-order yaw damper

A theoretical method of analyzing the effects of yaw-damper dynamics on the stability of an aircraft equipped with a second-order yaw damper

Date: December 1, 1952
Creator: Schy, Albert A & Gates, Ordway B , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical motions of hydrofoil systems

Theoretical motions of hydrofoil systems

Date: January 1, 1948
Creator: Imlay, Frederick H
Description: Results are presented of an investigation that has been undertaken to develop theoretical methods of treating the motions of hydrofoil systems and to determine some of the important parameters. Variations of parameters include three distributions of area between the hydrofoils, two rates of change of downwash angle with angle of attack, three depths of immersion, two dihedral angles, two rates of change of lift with immersion, three longitudinal hydrofoil spacings, two radii of gyration in pitching, and various horizontal and vertical locations of the center of gravity. Graphs are presented to show locations of the center of gravity for stable motion, values of the stability roots, and motions following the sudden application of a vertical force or a pitching moment to the hydrofoil system for numerous sets of values of the parameters.
Contributing Partner: UNT Libraries Government Documents Department
Theoretical motions of hydrofoil systems

Theoretical motions of hydrofoil systems

Date: June 1, 1947
Creator: Imlay, Frederick H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical Performance Characteristics of Sharp Lip Inlets at Subsonic Speeds

Theoretical Performance Characteristics of Sharp Lip Inlets at Subsonic Speeds

Date: September 1, 1953
Creator: Fradenburgh, Evan A & Wyatt, Demarquis D
Description: A method is presented for the estimation of the subsonic-flight-speed characteristics of sharp-lip inlets applicable to supersonic aircraft. The analysis, based on a simple momentum balance consideration, permits the computation of inlet pressure recovery - mass-flow relations and additive-drag coefficients for forward velocities from zero to the speed of sound. The penalties for operation of a sharp-lip inlet at velocity ratios other than 1.0 may be severe; at lower velocity ratios an additive drag is incurred that is not cancelled by lip suction, while at higher velocity ratios, unavoidable losses in inlet total pressure will result. In particular, at the take-off condition, the total pressure and the mass flow for a choked inlet are only 79 percent of the values ideally attainable with a rounded lip. Experimental data obtained at zero speed with a sharp-lip supersonic inlet model were in substantial agreement with the theoretical results.
Contributing Partner: UNT Libraries Government Documents Department
Theoretical performance characteristics of sharp-lip inlets at subsonic speeds

Theoretical performance characteristics of sharp-lip inlets at subsonic speeds

Date: January 1, 1954
Creator: Fradenburgh, Evan A & Demarquis, D Wyatt
Description: A method is presented for the estimation of the subsonic-flight-speed characteristics of sharp-lip inlets applicable to supersonic aircraft. The analysis, based on a simple momentum balance consideration, permits the computation of inlet-pressure-recovery mass-flow relations and additive-drag coefficients for forward velocities from zero to the speed of sound. The penalties for operation of a sharp-lip inlet at velocity ratios other than 1.0 may be severe; at lower velocity ratios an additive drag is incurred that is not cancelled by lip suction, while at higher velocity ratios, unavoidable losses in inlet total pressure will result. In particular, at the take-off condition, the total pressure and the mass flow for a choked inlet are only 79 percent of the values ideally attainable with a rounded lip. The test specimens were polished and unnotched. The manufacturer of the material, the Aluminum Company of America, has made axial-load tests on 24S-T4 and 75S-T6 rod material. The test techniques used at the three laboratories are described in detail; the test results are presented and are compared with each other and with results obtained on unpolished sheet by the National Bureau of Standards. Experimental data obtained at zero speed with a sharp-lip supersonic inlet model were in ...
Contributing Partner: UNT Libraries Government Documents Department
Theoretical performance of an axial-flow compressor in a gas-turbine engine operating with inlet water injection

Theoretical performance of an axial-flow compressor in a gas-turbine engine operating with inlet water injection

Date: March 1, 1952
Creator: Hensley, Reesc V
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical performance of JP-4 fuel and liquid oxygen as a rocket propellant I : frozen composition

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

Date: April 17, 1956
Creator: Huff, Vearl N & Fortini, Anthony
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical performance of JP-4 fuel and liquid oxygen as a rocket propellant II : equilibrium composition

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

Date: September 7, 1956
Creator: Huff, Vearl N; Fortini, Anthony & Gordon, Sanford
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.
Contributing 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 : equilibrium composition

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

Date: October 2, 1956
Creator: Gordon, Sanford & Huff, Vearl N
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.
Contributing Partner: UNT Libraries Government Documents Department