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 Decade: 1940-1949
 Year: 1947
 Serial/Series Title: NACA Technical Notes
 Collection: National Advisory Committee for Aeronautics Collection
The 1350 F stress-rupture properties of two wrought alloys and three cast alloys

The 1350 F stress-rupture properties of two wrought alloys and three cast alloys

Date: November 1947
Creator: Reynolds, E E; Freeman, J W & White, A E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Airfoil in sinusoidal motion in a pulsating stream

Airfoil in sinusoidal motion in a pulsating stream

Date: June 1, 1947
Creator: Greenberg, J Mayo
Description: The forces and moments on a two-dimensional airfoil executing harmonic motions in a pulsating stream are derived on the basis of non-stationary incompressible potential flow theory, with the inclusion of the effect of the continuous sheet of vortices shed from the trailing edge. An assumption as to the form of the wake is made with a certain degree of approximation. A comparison with previous work applicable only to the special case of a stationary airfoil is made by means of a numerical example, and the excellent agreement obtained shows that the wake approximation is quite sufficient. The results obtained are expected to be useful in considerations of forced vibrations and flutter of rotary wing aircraft.
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
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
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: 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
Axial-flow fan and compressor blade design data on 52.5 degrees stagger and further verification of cascade data by rotor tests

Axial-flow fan and compressor blade design data on 52.5 degrees stagger and further verification of cascade data by rotor tests

Date: April 1, 1947
Creator: Bogdonoff, Seymour M & Hess, Eugene E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Bearing strength of some sand-cast magnesium alloys

Bearing strength of some sand-cast magnesium alloys

Date: February 1, 1947
Creator: Moore, R L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Bending stresses due to torsion in a tapered box beam

Bending stresses due to torsion in a tapered box beam

Date: May 1, 1947
Creator: Kruszewski, Edwin T
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Boundary-induced upwash for yawed and swept-back wings in closed circular wind tunnels

Boundary-induced upwash for yawed and swept-back wings in closed circular wind tunnels

Date: May 1, 1947
Creator: Eisenstadt, Bertram J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Boundary-layer momentum equations for three-dimensional flow

Boundary-layer momentum equations for three-dimensional flow

Date: October 1, 1947
Creator: Tetervin, Neal
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Buckling stresses of simply supported rectangular flat plates in shear

Buckling stresses of simply supported rectangular flat plates in shear

Date: March 1, 1947
Creator: Stein, Manuel & Neff, John
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Calculation of compressible flows past aerodynamic shapes by use of the streamline curvature

Calculation of compressible flows past aerodynamic shapes by use of the streamline curvature

Date: June 1, 1947
Creator: Perl, W
Description: A simple approximate method is given for the calculation of isentropic irrotational flows past symmetrical airfoils, including mixed subsonic-supersonic flows. The method is based on the choice of suitable values for the streamline curvature in the flow field and the subsequent integration of the equations of motion. The method yields limiting solutions for potential flow. The effect of circulation is considered. A comparison of derived velocity distributions with existing results that are based on calculation to the third order in the thickness ratio indicated satisfactory agreement. The results are also presented in the form of a set of compressibility correction rules that lie between the Prandtl-Glauert rule and the von Karman-Tsien rule (approximately). The different rules correspond to different values of the local shape parameter square root sign YC sub a, in which Y is the ordinate and C sub a is the curvature at a point on an airfoil. Bodies of revolution, completely supersonic flows, and the significance of the limiting solutions for potential flow are also briefly discussed.
Contributing Partner: UNT Libraries Government Documents Department
The calculation of the heat required for wing thermal ice prevention in specified icing conditions

The calculation of the heat required for wing thermal ice prevention in specified icing conditions

Date: December 1, 1947
Creator: Neel, C. B., Jr.; Bergrun, N. R.; Jukoff, D. & Schlaff, B. A.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Calculation of the Heat Required for Wing Thermal Ice Prevention in Specified Icing Conditions

The Calculation of the Heat Required for Wing Thermal Ice Prevention in Specified Icing Conditions

Date: December 1, 1947
Creator: Bergrun, Norman R.; Jukoff, David; Schlaff, Bernard A. & Neel, Carr B., Jr.
Description: Flight tests were made in natural icing conditions with two 8-ft-chord heated airfoils of different sections. Measurements of meteorological variables conducive to ice formation were made simultaneously with the procurement of airfoil thermal data. The extent of knowledge on the meteorology of icing, the impingement of water drops on airfoil surfaces, and the processes of heat transfer and evaporation from a wetted airfoil surface have been increased to a point where the design of heated wings on a fundamental, wet-air basis now can be undertaken with reasonable certainty.
Contributing Partner: UNT Libraries Government Documents Department
Calculations of the supersonic wave drag of nonlifting wings with arbitrary sweepback and aspect ratio : wings swept behind the Mach lines

Calculations of the supersonic wave drag of nonlifting wings with arbitrary sweepback and aspect ratio : wings swept behind the Mach lines

Date: May 1, 1947
Creator: Harmon, Sidney M & Swanson, Margaret D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Changes found on run-in and scuffed surfaces of steel chrome plate, and cast iron

Changes found on run-in and scuffed surfaces of steel chrome plate, and cast iron

Date: October 1, 1947
Creator: Good, J N & Godfrey, Douglas
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Charts for determining the characteristics of sharp-nose airfoils in two-dimensional flow at supersonic speeds

Charts for determining the characteristics of sharp-nose airfoils in two-dimensional flow at supersonic speeds

Date: January 1, 1947
Creator: Ivey, H Reese; Stickle, George W & Schuettler, Alberta
Description: Solutions of the Hugoniot shock equations and Meyer expansion equations are plotted in such a manner as to permit the pressure distribution, the local Mach number, and the angles of shock waves on arbitrary sharp-nose airfoils at supersonic speeds to be obtained directly. (author).
Contributing Partner: UNT Libraries Government Documents Department
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