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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 28, 1947
Creator: Shaw, M.C. & Nussdorfer, T.J.
Description: An analysis of the operating characteristics of a full-floating 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 to verify some results of the analysis are reported. The floating sleeve can operate over a wide range of speeds for a given shaft speed, the exact value depending principally upon the ratio of clearances and upon the ratio of radii of the bearing. Lower operating temperatures at high rotative speeds are to be expected by using a full-floating bearing. This lower operating temperature would be obtained at the expense of the load-carrying capacity of the bearing if, for comparison, the clearances remain the same in both bearings. A full-floating bearing having the same load capacity as a conventional journal bearing may be designed if decreased clearances are allowable.
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
Analysis, Verification, and Application of Equations and Procedures for Design of Exhaust-Pipe Shrouds

Analysis, Verification, and Application of Equations and Procedures for Design of Exhaust-Pipe Shrouds

Date: December 1, 1947
Creator: Ellerbrock, Herman H.; Wcislo, Chester R. & Dexter, Howard E.
Description: Investigations were made to develop a simplified method for designing exhaust-pipe shrouds to provide desired or maximum cooling of exhaust installations. Analysis of heat exchange and pressure drop of an adequate exhaust-pipe shroud system requires equations for predicting design temperatures and pressure drop on cooling air side of system. Present experiments derive such equations for usual straight annular exhaust-pipe shroud systems for both parallel flow and counter flow. Equations and methods presented are believed to be applicable under certain conditions to the design of shrouds for tail pipes of jet engines.
Contributing Partner: UNT Libraries Government Documents Department
Analytical and experimental investigation of bolted joints

Analytical and experimental investigation of bolted joints

Date: October 1, 1947
Creator: Rosenfeld, Samuel J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Analytical comparison of a standard turbojet engine, a turbojet engine with a tail-pipe burner, and a ram-jet engine

Analytical comparison of a standard turbojet engine, a turbojet engine with a tail-pipe burner, and a ram-jet engine

Date: February 10, 1947
Creator: Krebs, Richard P & Palasics, John
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Analytical Treatment of Normal Condensation Shock

Analytical Treatment of Normal Condensation Shock

Date: July 1, 1947
Creator: Heybey
Description: The condensation of water vapor in an air consequences: acquisition of heat (liberated heat vaporization; loss of mass on the part of the flowing gas (water vapor is converted to liquid); change in the specific gas constants and of the ratio k of the specific heats (caused by change of gas composition). A discontinuous change of state is therefore connected with the condensation; schlieren photographs of supersonic flows in two-dimensional Laval nozzles show two intersecting oblique shock fronts that in the case of high humidities may merge near the point of intersection into one normal shock front.
Contributing Partner: UNT Libraries Government Documents Department
An Anaylsis of Control Requirements and Control Parameters for Direct-Coupled Turbojet Engines

An Anaylsis of Control Requirements and Control Parameters for Direct-Coupled Turbojet Engines

Date: January 1, 1947
Creator: Novik, David & Otto, Edward W.
Description: Requirements of an automatic engine control, as affected by engine characteristics, have been analyzed for a direct-coupled turbojet engine. Control parameters for various conditions of engine operation are discussed. A hypothetical engine control is presented to illustrate the use of these parameters. An adjustable speed governor was found to offer a desirable method of over-all engine control. The selection of a minimum value of fuel flow was found to offer a means of preventing unstable burner operation during steady-state operation. Until satisfactory high-temperature-measuring devices are developed, air-fuel ratio is considered to be a satisfactory acceleration-control parameter for the attainment of the maximum acceleration rates consistent with safe turbine temperatures. No danger of unstable burner operation exists during acceleration if a temperature-limiting acceleration control is assumed to be effective. Deceleration was found to be accompanied by the possibility of burner blow-out even if a minimum fuel-flow control that prevents burner blow-out during steady-state operation is assumed to be effective. Burner blow-out during deceleration may be eliminated by varying the value of minimum fuel flow as a function of compressor-discharge pressure, but in no case should the fuel flow be allowed to fall below the value required for steady-state burner operation.
Contributing Partner: UNT Libraries Government Documents Department
Application of an ultraviolet spectrophotometric method to the estimation of alkylnaphthalenes in 10 experimental jet-propulsion fuels

Application of an ultraviolet spectrophotometric method to the estimation of alkylnaphthalenes in 10 experimental jet-propulsion fuels

Date: April 30, 1947
Creator: Cleaves, Alden P & Carver, Mildred S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The application of high-temperature strain gauges to the measurements of vibratory stresses in gas-turbine buckets

The application of high-temperature strain gauges to the measurements of vibratory stresses in gas-turbine buckets

Date: April 1, 1947
Creator: Kemp, R H; Morgan, W C & Manson, S S
Description: The feasibility of measuring the vibration in the buckets of a gas turbine under service conditions of speed and temperature was determined by use of a high temperature wire strain gauge cemented to a modified supercharger turbine bucket. A high-temperature wire strain gauge and the auxiliary mechanical and electrical equipment developed for the investigation are described.
Contributing Partner: UNT Libraries Government Documents Department
An application of lifting-surface theory to the prediction of angle-of-attack hinge-moment parameters for aspect ratio 4.5 wings

An application of lifting-surface theory to the prediction of angle-of-attack hinge-moment parameters for aspect ratio 4.5 wings

Date: September 1, 1947
Creator: Jones, Arthur L; Flanagan, Mildred G & Sluder, Loma
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An application of statistical data in the development of gust-load criterions

An application of statistical data in the development of gust-load criterions

Date: April 1, 1947
Creator: Bland, Reginald B & Reisert, T D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Application of the analogy between water flow with a free surface and two-dimensional compressible gas flow

Application of the analogy between water flow with a free surface and two-dimensional compressible gas flow

Date: January 1, 1947
Creator: Orlin, W James; Lindner, Norman J & Butterly, Jack G
Description: The theory of the hydraulic analogy -- that is, the analogy between water flow with a free surface and two-dimensional compressible gas flow -- and the limitations and conditions of the analogy are discussed. A test was run using the hydraulic analogy as applied to the flow about circular cylinders of various diameters at subsonic velocities extending into the supercritical range. The apparatus and techniques used in this application are described and criticized. Reasonably satisfactory agreement of pressure distributions and flow fields existed between water and air flow about corresponding bodies. This agreement indicated the possibility of extending experimental compressibility research by new methods.
Contributing Partner: UNT Libraries Government Documents Department
Application of the analogy between water flow with a free surface and two-dimensional compressible gas flow

Application of the analogy between water flow with a free surface and two-dimensional compressible gas flow

Date: February 1, 1947
Creator: Orlin, W James; Lindner, Norman J & Bitterly, Jack G
Description: The theory of hydraulic analogy, that is, the analogy between water flow with a free surface and two-dimensional compressible gas flow and the limitations and conditions of the analogy are discussed. A test run was made using the hydraulic analogy as applied to the flow about circular cylinders at various diameters at subsonic velocities extending to the super critical range. The apparatus and techniques used in this application are described and criticized. Reasonably satisfactory agreement of pressure distributions and flow fields existed between water and airflow about corresponding bodies. This agreement indicated the possibility of extending experimental compressibility research by new methods.
Contributing Partner: UNT Libraries Government Documents Department
Appreciation and determination of the hydrodynamic qualities of seaplanes

Appreciation and determination of the hydrodynamic qualities of seaplanes

Date: May 1, 1947
Creator: Parkinson, John B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An approximate method for calculating the effect of surface roughness on the drag of an airplane

An approximate method for calculating the effect of surface roughness on the drag of an airplane

Date: July 23, 1947
Creator: Hall, Charles F & Fitzgerald, Fred F
Description: None
Contributing Partner: UNT Libraries Government Documents Department