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 Decade: 1940-1949
 Year: 1945
 Collection: National Advisory Committee for Aeronautics Collection
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
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
The development and application of high-critical-speed nose inlets

The development and application of high-critical-speed nose inlets

Date: July 1, 1945
Creator: Wright, John B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The use of geared spring tabs for elevator control

The use of geared spring tabs for elevator control

Date: February 1, 1945
Creator: Phillips, William H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Critical combinations of shear and transverse direct stress for an infinitely long flat plate with edges elastically restrained against rotation

Critical combinations of shear and transverse direct stress for an infinitely long flat plate with edges elastically restrained against rotation

Date: January 1, 1945
Creator: Houbolt, John C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of the performance of a turbosupercharged engine of an exhaust-gas-to-air heat exchanger for thermal ice prevention

Effect of the performance of a turbosupercharged engine of an exhaust-gas-to-air heat exchanger for thermal ice prevention

Date: August 1, 1945
Creator: Look, Bonne C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The knock-limited performance of S reference fuel plus 2 milliliters of triethylthallium per gallon

The knock-limited performance of S reference fuel plus 2 milliliters of triethylthallium per gallon

Date: November 1, 1945
Creator: Meyer, Carl L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An investigation of a thermal ice-prevention system for a C-46 cargo airplane V : effect of thermal system on airplane cruise performance

An investigation of a thermal ice-prevention system for a C-46 cargo airplane V : effect of thermal system on airplane cruise performance

Date: January 13, 1945
Creator: Selna, James
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An investigation of a thermal ice-prevention system for a C-46 cargo airplane VI : dry-air performance of thermal system at several twin- and single-engine operating conditions at various altitudes

An investigation of a thermal ice-prevention system for a C-46 cargo airplane VI : dry-air performance of thermal system at several twin- and single-engine operating conditions at various altitudes

Date: May 1, 1945
Creator: Kees, Harold L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation of the effects of spoilers on the characteristics of a low-drag airfoil equipped with a 0.25-chord slotted flap

Wind-tunnel investigation of the effects of spoilers on the characteristics of a low-drag airfoil equipped with a 0.25-chord slotted flap

Date: July 23, 1945
Creator: Holtzclaw, Ralph W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Ultraviolet spectrochemical analysis for aromatics in aircraft fuels

Ultraviolet spectrochemical analysis for aromatics in aircraft fuels

Date: March 1, 1945
Creator: Cleaves, Alden P
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An investigation of aircraft heaters XVIII : a design manual for exhaust gas and air heat exchangers

An investigation of aircraft heaters XVIII : a design manual for exhaust gas and air heat exchangers

Date: August 1945
Creator: Boelter, L. M. K.; Martinelli, R. C.; Romie, F. E. & Morrin, E. H.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Nitrided-steel piston rings for engines of high specific power

Nitrided-steel piston rings for engines of high specific power

Date: January 1, 1945
Creator: Schmiedlin, Ralph F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Visual studies of cylinder lubrication I : the lubrication of the piston skirt

Visual studies of cylinder lubrication I : the lubrication of the piston skirt

Date: September 1, 1945
Creator: Nussdorfer, Theodore
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An experimental investigation of rectangular exhaust-gas ejectors applicable for engine cooling

An experimental investigation of rectangular exhaust-gas ejectors applicable for engine cooling

Date: May 1, 1945
Creator: Bogatsky, Donald
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Fuel-evaporation loss as determined by the change in the specific gravity of the fuel in an aircraft fuel tank

Fuel-evaporation loss as determined by the change in the specific gravity of the fuel in an aircraft fuel tank

Date: May 1, 1945
Creator: Kramer, Walter E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A general representation for axial-flow fans and turbines

A general representation for axial-flow fans and turbines

Date: June 1, 1945
Creator: Tucker, M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Heat-transfer coefficients for air flowing in round tubes, in rectangular ducts, and around finned cylinders

Heat-transfer coefficients for air flowing in round tubes, in rectangular ducts, and around finned cylinders

Date: February 1, 1945
Creator: Drexel, Rober E & Mcadams, William H
Description: Report reviews published data and presents some new data on heat transfer to air flowing in round tubes, in rectangular ducts, and around finned cylinders. The available data for heat transfer to air in straight ducts of rectangular and circular cross section have been correlated in plots of Stanton number versus Reynolds number to provide a background for the study of the data for finned cylinders. Equations are recommended for both the streamlined and turbulent regions, and data are presented for the transition region between turbulent and laminar flow. Use of hexagonal ends on round tubes causes the characteristics of laminar flow to extend to high Reynolds numbers. Average coefficients for the entire finned cylinder have been calculated from the average temperature at the base of the fins and an equation which was derived to allow for the effectiveness of the fins. The available results for each finned cylinder are correlated herein in terms of graphs of Stanton number versus Reynolds number. In general, for a given Reynolds number, the Stanton number increases with increases in both spacing and width of the fins, and is apparently independent of cylinder diameter and temperature difference. For a given coefficient of heat transfer ...
Contributing Partner: UNT Libraries Government Documents Department
Summary of Airfoil Data

Summary of Airfoil Data

Date: January 1, 1945
Creator: Abbott, Ira H; Von Doenhoff, Albert E & Stivers, Louis, Jr
Description: The historical development of NACA airfoils is briefly reviewed. New data are presented that permit the rapid calculation of the approximate pressure distributions for the older NACA four-digit and five-digit airfoils by the same methods used for the NACA 6-series airfoils. The general methods used to derive the basic thickness forms for NACA 6 and 7-series airfoils together with their corresponding pressure distributions are presented. Detail data necessary for the application of the airfoils to wing design are presented in supplementary figures placed at the end of the paper. The report includes an analysis of the lift, drag, pitching-moment, and critical-speed characteristics of the airfoils, together with a discussion of the effects of surface conditions. Available data on high-lift devices are presented. Problems associated with lateral-control devices, leading-edge air intakes, and interference are briefly discussed, together with aerodynamic problems of application. (author).
Contributing Partner: UNT Libraries Government Documents Department
Effect of normal pressure on the critical compressive and shear stress of curved sheet

Effect of normal pressure on the critical compressive and shear stress of curved sheet

Date: March 1, 1945
Creator: Rafel, Norman & Sandlin, Charles W , Jr
Description: Results are presented of tests of two sets of 20 curved-sheet specimens to determine the effect of normal pressure on the critical compressive and shear stress of curved sheets. It was found that normal pressure raised the critical compressive and shear stress of curved sheets except when outward bulging occurred in compression, in which case the critical stress was lowered by normal pressure. (author).
Contributing Partner: UNT Libraries Government Documents Department
On two-dimensional flows of compressible fluids

On two-dimensional flows of compressible fluids

Date: January 1, 1945
Creator: Bergman, Stefan
Description: This report is devoted to the study of two-dimensional steady motion of a compressible fluid. It is shown that the complete flow pattern around a closed obstacle cannot be obtained by the method of Chaplygin. In order to overcome this difficulty, a formula for the stream-function of a two-dimensional subsonic flow is derived. The formula involves an arbitrary function of a complex variable and yields all possible subsonic flow patterns of certain types. Conditions are given so that the flow pattern in the physical plane will represent a flow around a closed curve. The formula obtained can be employed for the approximate determination of a subsonic flow around an obstacle. The method can be extended to partially supersonic flows.
Contributing Partner: UNT Libraries Government Documents Department
Graphical and analytical methods for the determination of a flow of a compressible fluid around an obstacle

Graphical and analytical methods for the determination of a flow of a compressible fluid around an obstacle

Date: January 1, 1945
Creator: Bergman, Stefan
Description: Chaplygin introduced the hodograph method in the theory of compressible fluid flows and developed a method for constructing stream functions of such flows. This method, which has been extensively used in investigation of compressible fluid flows, is limited in certain respects. The expression for the stream function obtained in this manner can represent only certain types of flow patterns. In general, flow patterns obtained in this way cannot represent the whole flow around an obstacle, but only a part of such a flow, and therefore several expressions are needed in order to obtain the whole flow. On the other hand, in many instances it is important to have a single expression representing the whole flow. Recently Von Karman and Tsien constructed more general types of stream functions, but only by replacing the true pressure density relation by the linear pressure-specific volume relation so that their method is essential limited to flows the maximum Mach number of which is not too large. In a companion report the author derived a new formula for stream functions based on the true pressure density relation. It is not subject to the limitations of the Chaplygin method. In the present report this formula is employed ...
Contributing Partner: UNT Libraries Government Documents Department
On a method of constructing two-dimensional subsonic compressible flows around closed profiles

On a method of constructing two-dimensional subsonic compressible flows around closed profiles

Date: January 1, 1945
Creator: Bers, Lipman
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Heat-transfer tests of aqueous ethylene glycol solutions in an electrically heated tube

Heat-transfer tests of aqueous ethylene glycol solutions in an electrically heated tube

Date: August 1, 1945
Creator: Bernardo, Everett & Eian, Carroll S
Description: As part of an investigation of the cooling characteristics of liquid-cooled engines, tests were conducted with an electrically heated single-tube heat exchanger to determine the heat-transfer characteristics of an-e-2 ethylene glycol and other ethylene glycol-water mixtures. Similar tests were conducted with water and commercial butanol (n-butyl alcohol) for check purposes. The results of tests conducted at an approximately constant liquid-flow rate of 0.67 pound per second (Reynolds number, 14,500 to 112,500) indicate that at an average liquid temperature 200 degrees f, the heat-transfer coefficients obtained using water, nominal (by volume) 30 percent-70 percent and 70 percent-30 percent glycol-water mixtures are approximately 3.8, 2.8, and 1.4 times higher, respectively, than the heat-transfer coefficients obtained using an-e-2 ethylene glycol.
Contributing Partner: UNT Libraries Government Documents Department
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