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  Partner: UNT Libraries Government Documents Department
 Decade: 1940-1949
 Year: 1945
 Collection: National Advisory Committee for Aeronautics Collection
Addition of heat to a compressible fluid in motion

Addition of heat to a compressible fluid in motion

Date: February 1, 1945
Creator: Hicks, Bruce L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An additional investigation of the high-speed lateral-control characteristics of spoilers

An additional investigation of the high-speed lateral-control characteristics of spoilers

Date: June 1, 1945
Creator: Summers, James
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a 1/8-scale powered model of a high-speed bomber with a dual pusher propeller aft of the empennage

Aerodynamic characteristics of a 1/8-scale powered model of a high-speed bomber with a dual pusher propeller aft of the empennage

Date: October 12, 1945
Creator: Schnurbusch, Alfred W.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic Characteristics of Four Republic Airfoil Sections from Tests in Langley Two-Dimensional Low-Turbulence Tunnels

Aerodynamic Characteristics of Four Republic Airfoil Sections from Tests in Langley Two-Dimensional Low-Turbulence Tunnels

Date: September 27, 1945
Creator: Klein, Milton M.
Description: Four airfoils sections, designed by the Republic Aviation Corporation for the root and tip sections of the XF-12 airplane, were tested in the Langley two-dimensional low-turbulence tunnels to obtain their aerodynamic characteristics. Lift characteristics were obtained at Reynolds numbers of 3,000,000, 6,000,000, 9,000,000, and 14,000,000, whereas drag characteristics were obtained at Reynolds numbers of 3,000,000, 6,000,000, and 9,000,000. Pressure distributions were obtained for one of the root sections for several angles of attack at a Reynolds number of 2,600,000. Comparison of the root section that appeared best from the tests with the corresponding NACA 65-series section shows the Republic section has a higher maximum lift and higher calculated critical speeds, but a higher minimum drag. In addition, with standard roughness applied to the leading edge, the maximum lift of the Republic airfoil is lower than that of the NACA airfoil. Comparison of the Republic tip section with the corresponding NACA 65-series section shows the Republic airfoil has a lower maximum lift and a higher minimum drag than the NACA airfoil. The calculated critical speeds of the Republic section are slightly higher than those of the NACA section.
Contributing Partner: UNT Libraries Government Documents Department
Air-consumption parameters for automatic mixture control of aircraft engines

Air-consumption parameters for automatic mixture control of aircraft engines

Date: January 1, 1945
Creator: Shames, Sidney J
Description: Data obtained from Navy calibration tests of an 18-cylinder, two-row, radial engine of 3350-cubic-inch displacement and a 14-cylinder, two-row, radial engine of 2600-cubic-inch displacement (carburetor types) were analyzed to show the correlation between the air consumption of these engines and the parameters that evaluate the air consumption from intake-manifold temperature and pressure, exhaust back pressure, and engine speed.
Contributing Partner: UNT Libraries Government Documents Department
Air-flow and performance characteristics of the engine-stage supercharger of a double-row radial aircraft engine I: effect of operating variables

Air-flow and performance characteristics of the engine-stage supercharger of a double-row radial aircraft engine I: effect of operating variables

Date: August 1, 1945
Creator: Mesrobian, John M.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Airspeed fluctuations as a measure of atmospheric turbulence

Airspeed fluctuations as a measure of atmospheric turbulence

Date: July 1, 1945
Creator: Tolefson, H B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Analysis and modification of theory for impact of seaplanes on water

Analysis and modification of theory for impact of seaplanes on water

Date: January 1, 1945
Creator: Mayo, Wilbur L
Description: An analysis of available theory on seaplane impact and a proposed modification thereto are presented. In previous methods the overall momentum of the float and virtual mass has been assumed to remain constant during the impact but the present analysis shows that this assumption is rigorously correct only when the resultant velocity of the float is normal to the keel. The proposed modification chiefly involves consideration of the fact that forward velocity of the seaplane float causes momentum to be passed into the hydrodynamic downwash (an action that is the entire consideration in the case of the planing float) and consideration of the fact that, for an impact with trim, the rate of penetration is determined not only by the velocity component normal to the keel but also by the velocity component parallel to the keel, which tends to reduce the penetration. Experimental data for planing, oblique impact, and vertical drop are used to show that the accuracy of the proposed theory is good.
Contributing Partner: UNT Libraries Government Documents Department
Analysis and modification of theory for impact of seaplanes on water

Analysis and modification of theory for impact of seaplanes on water

Date: December 1, 1945
Creator: Mayo, Wilbur L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An analysis of jet-propulsion systems making direct use of the working substance of a thermodynamic cycle

An analysis of jet-propulsion systems making direct use of the working substance of a thermodynamic cycle

Date: February 1, 1945
Creator: Rubert, Kennedy F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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