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 Decade: 1940-1949
 Year: 1947
 Month: August
 Collection: National Advisory Committee for Aeronautics Collection
Aerodynamic characteristics of a 45 degree swept-back wing with aspect ratio of 3.5 and NACA 2S-50(05)-50(05) airfoil sections

Aerodynamic characteristics of a 45 degree swept-back wing with aspect ratio of 3.5 and NACA 2S-50(05)-50(05) airfoil sections

Date: August 4, 1947
Creator: Proterra, Anthony J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Altitude-wind-tunnel investigation of thrust augmentation of a turbojet engine III : performance with tail-pipe burning in standard-size tail pipe

Altitude-wind-tunnel investigation of thrust augmentation of a turbojet engine III : performance with tail-pipe burning in standard-size tail pipe

Date: August 11, 1947
Creator: Fleming, William A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Combustion-efficiency investigation of special fuels in single tubular-type combustor at simulated altitude conditions

Combustion-efficiency investigation of special fuels in single tubular-type combustor at simulated altitude conditions

Date: August 15, 1947
Creator: Dittrich, Ralph T
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A comparison of flight test results on a scout-bomber airplane with 4.7 degree and with 10 degree geometric dihedral in the wing outer panels

A comparison of flight test results on a scout-bomber airplane with 4.7 degree and with 10 degree geometric dihedral in the wing outer panels

Date: August 1, 1947
Creator: Forsyth, Charles M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Concerning the Velocity of Evaporation of Small Droplets in a Gas Atmosphere

Concerning the Velocity of Evaporation of Small Droplets in a Gas Atmosphere

Date: August 1, 1947
Creator: Fuchs, N.
Description: The evaporation velocity of liquid droplets under various conditions is theoretically calculated and a number of factors are investigated which are neglected in carrying out the fundamental equation of Maxwell. It is shown that the effect of these factors at the small drop sizes and the small weight concentrations ordinarily occurring in fog can be calculated by simple corrections. The evaporation process can be regarded as quasi-stationary in most cases. The question at hand, and also the equivalent question of the velocity of growth of droplets in a supersaturated atmosphere, is highly significant in meteorology and for certain industrial purposes. Since the literature concerning this is very insufficient and many important aspects either are not considered at all or are reported incorrectly, it seems that a short discussion is not superfluous. A special consideration will be given to the various assumptions and neglections that are necessary in deriving the fundamental equation of Maxwell. The experimental work available, which is very insufficient and in part poorly dependable, can be used as an accurate check on the theory only in very few cases.
Contributing Partner: UNT Libraries Government Documents Department
Cones in Supersonic Flow

Cones in Supersonic Flow

Date: August 1, 1947
Creator: Hantzsche, W.
Description: In the case of cones in axially symmetric flow of supersonic velocity, adiabatic compression takes place between shock wave and surface of the cone. Interpolation curves betwen shock polars and the surface are therefore necessary for the complete understanding of this type of flow. They are given in the present report by graphical-numerical integration of the differential equation for all cone angles and airspeeds.
Contributing Partner: UNT Libraries Government Documents Department
Design charts for flat compression panels having longitudinal extruded Y-section stiffeners and comparison with panels having formed Z-section stiffeners

Design charts for flat compression panels having longitudinal extruded Y-section stiffeners and comparison with panels having formed Z-section stiffeners

Date: August 1, 1947
Creator: Dow, Norris F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Determination of Stress-Rupture Parameters for Four Heat-Resisting Alloys

Determination of Stress-Rupture Parameters for Four Heat-Resisting Alloys

Date: August 25, 1947
Creator: Lidman, William G.
Description: Stress-rupture data for four heat-resisting alloys are analyzed according to equations of the theory of rate processes. A method for determining the four parameters of structure and composition is demonstrated and the four parameters are determined for each of the alloys: forged S816, cast S816, cast S590, and cast Vitallium. It is concluded that parameters can be determined for an alloy provided sufficient reliable experimental data are available.
Contributing Partner: UNT Libraries Government Documents Department
The development of jet-engine Nacelles for a high-speed bomber design

The development of jet-engine Nacelles for a high-speed bomber design

Date: August 29, 1947
Creator: Dannenberg, Robert E
Description: The results of an experimental investigation made for the purpose of developing suitable jet-engine nacelle designs for a high-speed medium bomber are presented. Two types of nacelles were investigated, the first enclosing two 4000-pounds-thrust jet engines and a 65-inch-diameter landing wheel and the second enclosing a single 4000-pounds-thrust jet engine. Both types of nacelles were tested in positions underslung beneath the wing and centrally located on the wing. This report summarizes the investigation which was performed at low speed for the purpose of developing entrance and body shapes of suitable form. Included are results from the high-speed portion of the investigation on the characteristics of an underslung nacelle.
Contributing Partner: UNT Libraries Government Documents Department
Development of NACA submerged inlets and a comparison with wing leading-edge inlets for a 1/4-scale model of a fighter airplane

Development of NACA submerged inlets and a comparison with wing leading-edge inlets for a 1/4-scale model of a fighter airplane

Date: August 7, 1947
Creator: Mossman, Emmet A
Description: Characteristics of NACA submerged duct entries and wing leading-edge inlets designed for a 1/4 scale flow model of a fighter-type airplane powered by a jet engine in the fuselage are presented.
Contributing Partner: UNT Libraries Government Documents Department
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