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 Serial/Series Title: NACA Advanced Restricted Report
 Collection: National Advisory Committee for Aeronautics Collection
Application of a numerical procedure to stress analysis of stringer-reinforced panels

Application of a numerical procedure to stress analysis of stringer-reinforced panels

Date: March 1, 1945
Creator: Kempner, Joseph
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The application of data on strength under repeated stresses to the design of aircraft

The application of data on strength under repeated stresses to the design of aircraft

Date: October 1945
Creator: Grover, H. J.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Application of spring tabs to elevator controls

Application of spring tabs to elevator controls

Date: October 1, 1944
Creator: Phillips, William H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Application of the method of least squares to engine-cooling analysis

Application of the method of least squares to engine-cooling analysis

Date: August 1, 1944
Creator: Corson, Blake W , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Artificial running-in of piston rings

Artificial running-in of piston rings

Date: March 1, 1944
Creator: Machlin, E S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Bending and shear stresses developed by the instantaneous arrest of the root of a cantilever beam rotating with constant angular velocity about a transverse axis through the root

Bending and shear stresses developed by the instantaneous arrest of the root of a cantilever beam rotating with constant angular velocity about a transverse axis through the root

Date: June 1, 1945
Creator: Stowell, Elbridge Z; Schwartz, Edward B & Houbolt, John C
Description: A theoretical investigation was made of the behavior of a cantilever beam in rotational motion about a transverse axis through the root determining the stresses, the deflections, and the accelerations that occur in the beam as a result of the arrest of motion. The equations for bending and shear stress reveal that, at a given percentage of the distance from root to tip and at a given trip velocity, the bending stresses for a particular mode are independent of the length of the beam and the shear stresses vary inversely with the length. When examined with respect to a given angular velocity instead of a given tip velocity, the equations reveal that the bending stress is proportional to the length of the beam whereas the shear stress is independent of the length. Sufficient experimental verification of the theory has previously been given in connection with another problem of the same type.
Contributing Partner: UNT Libraries Government Documents Department
Bending and shear stresses developed by the instantaneous arrest of the root of a moving cantilever beam

Bending and shear stresses developed by the instantaneous arrest of the root of a moving cantilever beam

Date: November 1, 1944
Creator: Houbolt, John C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Breaking aircraft-engine oil foams by use of electrically charged condenser plates

Breaking aircraft-engine oil foams by use of electrically charged condenser plates

Date: November 1, 1944
Creator: Pinkel, I Irving
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Calculations of economy of 18-cylinder radial aircraft engine with exhaust-gas turbine geared to the crankshaft at cruising speed

Calculations of economy of 18-cylinder radial aircraft engine with exhaust-gas turbine geared to the crankshaft at cruising speed

Date: January 1, 1945
Creator: Zimmerman, Richard H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Calculations of the Performance of a Compression-Ignition Engine-Compressor Turbine Combination I : Performance of a Highly Supercharged Compression-Ignition Engine

Calculations of the Performance of a Compression-Ignition Engine-Compressor Turbine Combination I : Performance of a Highly Supercharged Compression-Ignition Engine

Date: December 1, 1945
Creator: Sanders, J. C. & Mendelson, Alexander
Description: Small high-speed single-cylinder compression-ignition engines were tested to determine their performance characteristics under high supercharging. Calculations were made on the energy available in the exhaust gas of the compression-ignition engines. The maximum power at any given maximum cylinder pressure was obtained when the compression pressure was equal to the maximum cylinder pressure. Constant-pressure combustion was found possible at an engine speed of 2200 rpm. Exhaust pressures and temperatures were determined from an analysis of indicator cards. The analysis showed that, at rich mixtures with the exhaust back pressure equal to the inlet-air pressure, there is excess energy available for driving a turbine over that required for supercharging. The presence of this excess energy indicates that a highly supercharged compression-ignition engine might be desirable as a compressor and combustion chamber for a turbine.
Contributing Partner: UNT Libraries Government Documents Department
Charts for calculation of the critical compressive stress for local instability of idealized web- and T-stiffened panels

Charts for calculation of the critical compressive stress for local instability of idealized web- and T-stiffened panels

Date: August 1, 1944
Creator: Baab, George W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Charts for calculation of the critical stress for local instability of columns with I-, Z-, channel and rectangular-tube section

Charts for calculation of the critical stress for local instability of columns with I-, Z-, channel and rectangular-tube section

Date: November 1, 1943
Creator: Heimerl, George J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Charts for critical combinations of longitudinal and transverse direct stress for flat rectangular plates

Charts for critical combinations of longitudinal and transverse direct stress for flat rectangular plates

Date: March 1, 1946
Creator: Stein, Manuel
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Charts for determining jet-boundary corrections for complete models in 7- by 10-foot closed rectangular wind tunnels

Charts for determining jet-boundary corrections for complete models in 7- by 10-foot closed rectangular wind tunnels

Date: September 1, 1945
Creator: Gray, Joseph L , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Charts for the minimum-weight design of 24S-T aluminum-alloy flat compression panels with longitudinal Z-section stiffeners

Charts for the minimum-weight design of 24S-T aluminum-alloy flat compression panels with longitudinal Z-section stiffeners

Date: August 1, 1945
Creator: Schuette, Evan H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Column and plate compressive strengths of aircraft structural materials : 17S-T aluminum-alloy sheet

Column and plate compressive strengths of aircraft structural materials : 17S-T aluminum-alloy sheet

Date: June 1, 1945
Creator: Roy, J Albert
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Column and Plate Compressive Strengths of Aircraft Structural Materials: 24S-T Aluminum-alloy Sheet

Column and Plate Compressive Strengths of Aircraft Structural Materials: 24S-T Aluminum-alloy Sheet

Date: June 1, 1945
Creator: Lundquist, Eugene E.; Schuette, Evan H.; Heimerl, George J. & Roy, J. Albert
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Column and plate compressive strengths of aircraft structural materials : extruded 14S-T aluminum alloy

Column and plate compressive strengths of aircraft structural materials : extruded 14S-T aluminum alloy

Date: May 1, 1946
Creator: Niles, Donald E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Column and plate compressive strengths of aircraft structural materials : extruded 24S-T aluminum alloy

Column and plate compressive strengths of aircraft structural materials : extruded 24S-T aluminum alloy

Date: July 1, 1945
Creator: Roy, J Albert
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Column and Plate Compressive Strengths of Aircraft Structural Materials: Extruded 24S-T Aluminum Alloy

Column and Plate Compressive Strengths of Aircraft Structural Materials: Extruded 24S-T Aluminum Alloy

Date: July 1, 1945
Creator: Heimerl, George J. & Roy, J Albert
Description: Column and plate compressive strengths of extruded 24S-T aluminum alloy were determined both within and beyond the elastic range from tests of thin-strip columns and local-instability tests of H-, Z-,and channel-section columns. These tests are part of an extensive research investigation to provide data on the' structural strength of various aircraft materials. The results are presented in the form of curves and charts that are suitable for use in the design and analysis of aircraft structures.
Contributing Partner: UNT Libraries Government Documents Department
Column and plate compressive strengths of aircraft structural materials : extruded 75S-T aluminum alloy

Column and plate compressive strengths of aircraft structural materials : extruded 75S-T aluminum alloy

Date: July 1, 1945
Creator: Roy, J Albert
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Column and plate compressive strengths of aircraft structural materials : extruded R303-T aluminum alloy

Column and plate compressive strengths of aircraft structural materials : extruded R303-T aluminum alloy

Date: October 1, 1945
Creator: Fay, Douglas P
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Comparative cooling of cylinders of nonuniform fin width with tight-fitting baffles and with baffles that provide constant flow-path areas

Comparative cooling of cylinders of nonuniform fin width with tight-fitting baffles and with baffles that provide constant flow-path areas

Date: April 1, 1944
Creator: Buckner, Howard A , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A comparative study of the effect of wing flutter shape on the critical flutter speed

A comparative study of the effect of wing flutter shape on the critical flutter speed

Date: November 1, 1943
Creator: Pinkel, I Irving
Description: None
Contributing Partner: UNT Libraries Government Documents Department