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 Decade: 1940-1949
 Year: 1947
 Collection: National Advisory Committee for Aeronautics Collection
Altitude-wind-tunnel investigation of thrust augmentation of a turbojet engine II : performance with water injection at compressor inlet

Altitude-wind-tunnel investigation of thrust augmentation of a turbojet engine II : performance with water injection at compressor inlet

Date: May 19, 1947
Creator: Dietz, Robert O & Fleming, William A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Altitude-wind-tunnel investigation of thrust augmentation of a turbojet engine III : performance with tail-pipe burning in standard-size tail pipe

Altitude-wind-tunnel investigation of thrust augmentation of a turbojet engine III : performance with tail-pipe burning in standard-size tail pipe

Date: August 11, 1947
Creator: Fleming, William A & Golladay, Richard L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An analysis of airspeeds and Mach numbers attained by Lockheed Constellation airplanes in transcontinental operations during the early summer of 1946

An analysis of airspeeds and Mach numbers attained by Lockheed Constellation airplanes in transcontinental operations during the early summer of 1946

Date: October 10, 1947
Creator: Steiner, Roy
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Analysis of jet-propulsion-engine combustion-chamber pressure losses

Analysis of jet-propulsion-engine combustion-chamber pressure losses

Date: January 1, 1947
Creator: Pinkel, I Irving & Shames, Harold
Description: The development and the use of a chart for estimating the pressure losses in jet-engine combustion chambers are described. By means of the chart, the pressure losses due to fluid friction and to momentum changes in the air flow accompanying combustion can be separately evaluated. The pressure-loss chart is based on the assumption that the pressure losses in the actual combustion chamber can be matched by those of an equivalent combustion chamber of constant cross-sectional area. The concept of the equivalent combustion chamber serves as a convenient basis for comparing the pressure-loss characteristics of combustion chambers of a variety of designs. The over-all pressure losses computed from the pressure-loss chart are within 7 percent of the experimental values for the three types of combustion chambers considered herein.
Contributing Partner: UNT Libraries Government Documents Department
An analysis of longitudinal-control problems encountered in flight at transonic speeds with a jet-propelled airplane

An analysis of longitudinal-control problems encountered in flight at transonic speeds with a jet-propelled airplane

Date: September 25, 1947
Creator: Brown, Harvey H; Rolls, L Stewart & Clousing, Lawrence A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Analysis of performance of jet engine from characteristics of components I : aerodynamic and matching characteristics of turbine component determined with cold air

Analysis of performance of jet engine from characteristics of components I : aerodynamic and matching characteristics of turbine component determined with cold air

Date: January 1, 1947
Creator: Goldstein, Arthur W
Description: The performance of the turbine component of an NACA research jet engine was investigated with cold air. The interaction and the matching of the turbine with the NACA eight-stage compressor were computed with the combination considered as a jet engine. The over-all performance of the engine was then determined. The internal aerodynamics were studied to the extent of investigating the performance of the first stator ring and its influence on the turbine performance. For this ring, the stream-filament method for computing velocity distribution permitted efficient sections to be designed, but the design condition of free-vortex flow with uniform axial velocities was not obtained.
Contributing Partner: UNT Libraries Government Documents Department
Analysis of performance of jet engine from characteristics of components I : aerodynamic and matching characteristics of turbine component determined with cold air

Analysis of performance of jet engine from characteristics of components I : aerodynamic and matching characteristics of turbine component determined with cold air

Date: October 1, 1947
Creator: Goldstein, Arthur W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An analysis of the compressive strength of honeycomb cores for sandwich construction

An analysis of the compressive strength of honeycomb cores for sandwich construction

Date: January 1, 1947
Creator: Norris, Charles B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An analysis of the factors that affect the exhaust process of a four-stroke-cycle reciprocating engine

An analysis of the factors that affect the exhaust process of a four-stroke-cycle reciprocating engine

Date: April 1, 1947
Creator: Stanitz, John D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An analysis of the full-floating journal bearing

An analysis of the full-floating journal bearing

Date: January 1, 1947
Creator: Shaw, M C & Nussdorfer, T J , Jr
Description: An analysis of the operating characteristics of a full-floating journal bearing, a bearing in which a floating sleeve is located between the journal and bearing surfaces, is presented together with charts from which the performance of such bearings may be predicted. Examples are presented to illustrate the use of these charts and a limited number of experiments conducted upon a glass full-floating bearing are reported to verify some results of the analysis.
Contributing Partner: UNT Libraries Government Documents Department