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 Serial/Series Title: NACA Advanced Restricted Report
 Collection: National Advisory Committee for Aeronautics Collection
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
Comparison between calculated and measured loads on wing and horizontal tail in pull-up maneuvers

Comparison between calculated and measured loads on wing and horizontal tail in pull-up maneuvers

Date: October 1, 1945
Creator: Matheny, Cloyce E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Comparison of an approximate and an exact method of shear-lag analysis

Comparison of an approximate and an exact method of shear-lag analysis

Date: January 1, 1944
Creator: Duberg, John E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A comparison of analytically and experimentally determined isothermal pressure losses in a heat-exchanger installation

A comparison of analytically and experimentally determined isothermal pressure losses in a heat-exchanger installation

Date: May 1, 1945
Creator: Hillendahl, Wesley H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Comparison of tail and wing-tip spin-recovery parachutes as determined by tests in the Langley 20-foot free-spinning tunnel

Comparison of tail and wing-tip spin-recovery parachutes as determined by tests in the Langley 20-foot free-spinning tunnel

Date: March 1, 1946
Creator: Malvestuto, Frank S , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A comparison of the effects of four-blade dual- and single-rotation propellers on the stability and control characteristics of a high-powered single-engine airplane

A comparison of the effects of four-blade dual- and single-rotation propellers on the stability and control characteristics of a high-powered single-engine airplane

Date: June 1, 1944
Creator: Wick, Bradford M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A comparison of two flight-test procedures for the determination of aileron control capabilities of an airplane

A comparison of two flight-test procedures for the determination of aileron control capabilities of an airplane

Date: July 1, 1945
Creator: Skoog, Richard B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Comparison of Wind-Tunnel and Flight Measurements of Stability and Control Characteristics of a Douglas A-26 Airplane

Comparison of Wind-Tunnel and Flight Measurements of Stability and Control Characteristics of a Douglas A-26 Airplane

Date: March 1, 1946
Creator: Koven, William & Kayten, Gerald G.
Description: Tests in Langley pressure tunnel of model XA-26 bomber were compared with those of A-26B (twin-engine attack bomber) and showed that static longitudinal stability, indicated by elevator-fixed neutral points, and variation of elevator deflection in straight and turning flight were good. Airplane possessed improved stability at low speeds which was attributed to pronounced stalling at root of production wing. At rudder-force reversal at speeds higher than those in flight tests, agreement in rudder-fixed and rudder-free static directional stability was good. Hinge moment obtained at zero sideslip was satisfactory for determining aileron forces in sideslip.
Contributing Partner: UNT Libraries Government Documents Department
Comparisons of methods of computing bending moments in helicopter rotor blades in the plane of flapping

Comparisons of methods of computing bending moments in helicopter rotor blades in the plane of flapping

Date: August 1, 1945
Creator: Luecker, Arthur R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Compressibility and heating effects on pressure loss and cooling of a baffled cylinder barrel

Compressibility and heating effects on pressure loss and cooling of a baffled cylinder barrel

Date: July 1, 1944
Creator: Ellerbrock, Herman H , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Compressibility Effects on Heat Transfer and Pressure Drop in Smooth Cylindrical Tubes

Compressibility Effects on Heat Transfer and Pressure Drop in Smooth Cylindrical Tubes

Date: October 1, 1944
Creator: Nielsen, Jack N
Description: An analysis is made to simplify pressure-drop calculations for nonadiabatic and adiabatic friction flow of air in smooth cylindrical tubes when the density changes due to heat transfer and pressure drop are appreciable. Solutions of the equation of motion are obtained by the use of Reynolds' analogy between heat transfer and skin friction. Charts of the solutions are presented for making pressure-drop calculations. A technique of using the charts to determine the position of a normal shock in a tube is described.
Contributing Partner: UNT Libraries Government Documents Department