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 Serial/Series Title: NACA Advanced Restricted Report
 Collection: National Advisory Committee for Aeronautics Collection
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
Compressible potential flow with circulation about a circular cylinder

Compressible potential flow with circulation about a circular cylinder

Date: January 1, 1944
Creator: Heaslet, Max A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Compressive Strength of Flat Panels with Z- and Hat-Section Stiffeners

Compressive Strength of Flat Panels with Z- and Hat-Section Stiffeners

Date: June 1, 1944
Creator: Kotanchik, Joseph; Weinberger, Robert A.; Zender, George W. & Neff, John, Jr.
Description: Compression tests were conducted on 247 panels with Z-section stiffeners and 304 panels with hat-section stiffeners. Specimens were constructed from artificially aged Alclad 24S aluminum alloy with minimum guaranteed yield strengths of 64 and 57 ksi for stiffeners and sheet materials, respectively. Height, thickness, and spacing of stiffeners, sheet thickness, and length of specimens were varied systematically to show effects of changes in these dimensions on panel strength. Results show average stresses at buckling load and maximum load.
Contributing Partner: UNT Libraries Government Documents Department
Compressive strength of flat panels with Z-section stiffeners

Compressive strength of flat panels with Z-section stiffeners

Date: February 1, 1944
Creator: Dobrowski, Charles V
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The conformal transformation of an airfoil into a straight line and its application to the inverse problem of airfoil theory

The conformal transformation of an airfoil into a straight line and its application to the inverse problem of airfoil theory

Date: December 1, 1944
Creator: Mutterperl, William
Description: A method of conformal transformation is developed that maps an airfoil into a straight line, the line being chosen as the extended chord line of the airfoil. The mapping is accomplished by operating directly with the airfoil ordinates. The absence of any preliminary transformation is found to shorten the work substantially over that of previous methods. Use is made of the superposition of solutions to obtain a rigorous counterpart of the approximate methods of thin-airfoils theory. The method is applied to the solution of the direct and inverse problems for arbitrary airfoils and pressure distributions. Numerical examples are given. Applications to more general types of regions, in particular to biplanes and to cascades of airfoils, are indicated. (author).
Contributing Partner: UNT Libraries Government Documents Department
Construction of wire strain gages for engine application

Construction of wire strain gages for engine application

Date: December 1, 1943
Creator: Tucker, Maurice
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Continuous use of internal cooling to suppress knock in aircraft engines cruising at high power

Continuous use of internal cooling to suppress knock in aircraft engines cruising at high power

Date: August 1, 1944
Creator: Bell, Arthur H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A cooling correlation of the Wright R-2600-8 engine showing the effect of water as an internal coolant

A cooling correlation of the Wright R-2600-8 engine showing the effect of water as an internal coolant

Date: February 1, 1945
Creator: Engelman, Helmuth W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Correlation of exhaust-valve temperatures with engine operating conditions and valve design

Correlation of exhaust-valve temperatures with engine operating conditions and valve design

Date: January 1, 1945
Creator: Sanders, J C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A correlation of loadings and afterbody length-beam ratios of various flying-boat hulls

A correlation of loadings and afterbody length-beam ratios of various flying-boat hulls

Date: June 1, 1946
Creator: Parkinson, John B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Correlation of single-cylinder cooling tests of a Pratt and Whitney R-2800-21 engine cylinder with wind-tunnel tests of a Pratt and Whitney R-2800-27 engine

Correlation of single-cylinder cooling tests of a Pratt and Whitney R-2800-21 engine cylinder with wind-tunnel tests of a Pratt and Whitney R-2800-27 engine

Date: December 1, 1943
Creator: Rollin, Vern G
Description: None
Contributing Partner: UNT Libraries Government Documents Department