You limited your search to:

 Collection: Technical Report Archive and Image Library
A theoretical analysis of the performance of a diesel engine-compressor-turbine combination for aircraft

A theoretical analysis of the performance of a diesel engine-compressor-turbine combination for aircraft

Date: April 1, 1945
Creator: Hall, Eldon W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical analysis of the performance of a supersonic ducted rocket

Theoretical analysis of the performance of a supersonic ducted rocket

Date: February 13, 1948
Creator: Hensley, Reece V
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical analysis of total-pressure loss and airflow distribution for tubular turbojet combustors with constant annulus and liner cross-sectional areas

Theoretical analysis of total-pressure loss and airflow distribution for tubular turbojet combustors with constant annulus and liner cross-sectional areas

Date: January 1, 1958
Creator: Graves, Charles C & Grobman, Jack S
Description: Compressible and incompressible flow calculations were made of the combustor total-pressure-loss coefficient and liner airflow distribution for tubular turbojet combustors having constant annulus and liner cross-sectional areas along the combustor axis. Information on static and total pressure distribution and liner air-jet entrance angles along the length of the combustor was obtained as an intermediate step in the calculations. The calculations include the effects of heat release, annulus wall friction, and variation in discharge coefficients of the liner wall openings along the combustor. The combustor total-pressure-loss coefficient and liner air-flow distribution are presented graphically in terms of the following dimensionless parameters: (1) combustor reference Mach number, (2) ratio of combustor-exit to inlet total temperature, (3) fraction of total airflow passing through the liner dome, (4) ratio of total open hole area in liner wall to total combustor cross-sectional area, and (5) ratio of liner cross-sectional area to total combustor cross-sectional area.
Contributing Partner: UNT Libraries Government Documents Department
Theoretical analysis of various thrust-augmentation cycles for turbojet engines

Theoretical analysis of various thrust-augmentation cycles for turbojet engines

Date: January 1, 1950
Creator: Lundin, Bruce T
Description: The results of analytical studies of tail-pipe-burning, water-injection, and bleedoff methods of thrust augmentation are presented that provide an insight into the operating characteristics of these augmentation methods and summarizes the performance that may be obtained when applied to a typical turbojet engine. A brief description of the principles of operation of each augmentation method is given, together with curves that illustrate the effects of the principal design and operating variables of the augmentation system on the thrust and the liquid consumption of the engine. The necessity of designing tail-pipe burners with a low burner-inlet velocity, a low burner drag, and a high diffuser efficiency in order to obtain a high thrust augmentation and to minimize the loss in engine performance during nonburning operation is illustrated.
Contributing Partner: UNT Libraries Government Documents Department
Theoretical analysis of various thrust-augmentation cycles for turbojet engines

Theoretical analysis of various thrust-augmentation cycles for turbojet engines

Date: May 1, 1950
Creator: Lundin, Bruce T
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical and analog studies of the effects of nonlinear stability derivatives on the longitudinal motions of an aircraft in response to step control deflections and to the influence of proportional automatic control

Theoretical and analog studies of the effects of nonlinear stability derivatives on the longitudinal motions of an aircraft in response to step control deflections and to the influence of proportional automatic control

Date: January 1, 1955
Creator: Curfman, Howard J , Jr
Description: Through theoretical and analog results the effects of two nonlinear stability derivatives on the longitudinal motions of an aircraft have been investigated. Nonlinear functions of pitching-moment and lift coefficients with angle of attack were considered. Analog results of aircraft motions in response to step elevator deflections and to the action of the proportional control systems are presented. The occurrence of continuous hunting oscillations was predicted and demonstrated for the attitude stabilization system with proportional control for certain nonlinear pitching-moment variations and autopilot adjustments.
Contributing Partner: UNT Libraries Government Documents Department
Theoretical and experimental analysis of low-drag supersonic inlets having a circular cross section and a central body at Mach numbers 3.30, 2.75, and 2.45

Theoretical and experimental analysis of low-drag supersonic inlets having a circular cross section and a central body at Mach numbers 3.30, 2.75, and 2.45

Date: January 1, 1954
Creator: Ferri, Antonio & Nucci, Louis M
Description: Contains theoretical and experimental analysis of circular inlets having a central body at Mach numbers of 3.30, 2.75, and 2.45. The inlets have been designed in order to have low drag and high pressure recovery. The pressure recoveries obtained are of the same order of magnitude as those previously obtained by inlets having very large external drag.
Contributing Partner: UNT Libraries Government Documents Department
Theoretical and experimental analysis of low-drag supersonic inlets having a circular cross section and a central body at Mach numbers of 3.30, 2.75, and 2.45

Theoretical and experimental analysis of low-drag supersonic inlets having a circular cross section and a central body at Mach numbers of 3.30, 2.75, and 2.45

Date: November 10, 1948
Creator: Ferri, Antonio & Nucci, Louis M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical and experimental analysis of one-dimensional compressible flow in a rotating radial-inlet impeller channel

Theoretical and experimental analysis of one-dimensional compressible flow in a rotating radial-inlet impeller channel

Date: April 1, 1952
Creator: Lieblein, Seymour
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical and experimental analysis of the reduction of rotor blade vibration in turbomachinery through the use of modified stator vane spacing

Theoretical and experimental analysis of the reduction of rotor blade vibration in turbomachinery through the use of modified stator vane spacing

Date: September 1, 1958
Creator: Kemp, Richard H; Hirschberg, Marvin H & Morgan, William C
Description: None
Contributing Partner: UNT Libraries Government Documents Department