UNT Libraries Government Documents Department - 10 Matching Results

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Solvent Extraction

Description: Report discussing methods and theories of solvent extraction. Factors that influence solvent extraction, such as the distribution coefficient, relative solubility, and physical properties of the solvent, are discussed as well.
Date: July 18, 1947
Creator: Smellie, Robert H., Jr. & Krause, D. P.
Item Type: Refine your search to only Report
open access

Further experiments on the flow and heat transfer in a heated turbulent air jet

Description: "Measurements have been made of the mean-total-head and mean-temperature fields in a round turbulent jet with various initial temperatures. The results show that the jet spreads more rapidly as its density becomes lower than that of the receiving medium, even when the difference is not sufficiently great to cause dynamic-pressure function. Rough analytical considerations have given the same relative spread. The effective "turbulent Prandtl number" for a section of the fully developed jet was fo… more
Date: August 18, 1947
Creator: Corrsin, Stanley & Uberoi, Mahinder S.
Item Type: Refine your search to only Report
open access

A Time History of Control Operation of a C-54 Airplane in Blind Landing Approaches

Description: "Tests were made with a C-54 airplane in which airline pilots made several blind approaches to determine whether any special flying techniques were used in blind landings and whether any special handling-qualities requirements would have to be formulated because of such special techniques. It was found that the airplane was flown at all times in the normal manner; that is, all turns were banked turns that were nearly coordinated by use of the rudder so that the sideslip was held close to zero. … more
Date: July 18, 1947
Creator: Talmage, Donald B.
Item Type: Refine your search to only Report
open access

Cooling of Gas Turbines, 2, Effectiveness of Rim Cooling of Blades

Description: An analysis is presented of rim cooling of gas-turbine blades; that is, reducing the temperature at the base of the blade (wheel rim), which cools the blade by conduction alone. Formulas for temperature and stress distributions along the blade are derived and, by the use of experimental stress-rupture data for a typical blade alloy, a relation is established between blade life (time for rupture), operating speed, and amount of rim cooling for several gas temperatures. The effect of blade parame… more
Date: March 18, 1947
Creator: Wolfenstein, Lincoln; Meyer, Gene L. & McCarthy, John S.
Item Type: Refine your search to only Report
open access

An Investigation of the Aerodynamic Characteristics of an 0.08-Scale Model of the Chance Vought XF7U-1 Airplane in the Langley High-Speed 7- by 10-Foot Tunnel: Part II - Basic Lateral Stability Characteristics TED No. NACA DE308, Part 2, Basic Lateral Stability Charactistics, TED No. NACA DE308

Description: Tests have been conducted in the Langley high-speed 7- by 10-foot tunnel over a Mach number range from 0.40 to 0.91 to determine the stability and control characteristics of an 0.08-scale model of the Chance Vought XF7U-1 airplane. The basic lateral stability characteristics of the complete model with undeflected control surfaces are presented in the present report with a very limited analysis of the results.
Date: July 18, 1947
Creator: Kemp, William B., Jr.; Goodson, Kenneth W. & Kuhn, Richard E.
Item Type: Refine your search to only Report
open access

Cooling of Gas Turbines, 4 - Calculated Temperature Distribution in the Trailing Part of a Turbine Blade Using Direct Liquid Cooling

Description: A theoretical analysis of the temperature distribution through the trailing portion of a blade near the coolant passages of liquid cooled gas turbines was made. The analysis was applied to obtain the hot spot temperatures at the trailing edge and influence of design variables. The effective gas temperature was varied from 2000 degrees to 5000 degrees F in each investigation.
Date: April 18, 1947
Creator: Brown, W. Byron & Monroe, William R.
Item Type: Refine your search to only Report
open access

Free-Spinning-Tunnel Tests of a 1/35-Scale Model of the Douglas XB-43 Airplane

Description: Spin tests have been performed in the Langley 20-foot free-spinning tunnel on a 1/35-scale model of the Douglas XB-43 airplane. The spin and recovery characteristics were determined for several loading conditions of the airplane. The effects of installing a dorsal fin and of installing a ventral fin were investigated. Emergency escape of the crew was simulated and the stick and rudder pedal forces necessary to effect recoveries on the airplane were determined.
Date: July 18, 1947
Creator: Snyder, Thomas L.
Item Type: Refine your search to only Report
open access

An Investigation of the Aerodynamic Characteristics of an 0.08-Scale Model of the Chance Vought XF7U-1 Airplane in the Langley High-Speed 7- by 10-Foot Tunnel: Part I - Basic Longitudinal Stability Characteristics, TED No. NACA DE308, Part 1, Basic Longitudinal Stability Characteristics, TED No. NACA DE308

Description: The stability and control characteristics of an 0.08-scale model of the Chance Vought XF7U-1 airplane have been investigated over a Mach number range from 0.40 to 0.91. Results of the basic longitudinal tests of the complete model with undeflected control surfaces are given in the present report with a very limited analysis of the results.
Date: July 18, 1947
Creator: Kemp, William B., Jr.; Kuhn, Richard E. & Goodson, Kenneth W.
Item Type: Refine your search to only Report
open access

The Linear Perturbation Theory of Axially Symmetric Compressible Flow With Application to the Effect of Compressibility on the Pressure Coefficient at the Surface of a Body of Revolution

Description: Memorandum discussing four related methods for the study of compressible flow by means of the linear perturbation theory for the case of three-dimensional flow with axial symmetry. A general method which includes the other is also discussed briefly. In each case, the properties of the compressible flow are obtained from those of a corresponding incompressible flow.
Date: July 18, 1947
Creator: Herriot, John G.
Item Type: Refine your search to only Report
open access

A Preliminary Theoretical Study of Aerodynamic Instability of a Two-Blade Helicopter Rotor

Description: Report presenting numerical results of flutter calculations for a two-blade helicopter using a see-saw-type rotor. The stability condition for oscillatory motion is expressed in terms of a small number of composite parameters that are evaluated from moments of inertia, angle settings, and aerodynamic parameters of a blade. The analysis indicated that a see-saw rotor with a coning angle is more unstable than an airplane wing with the same parameters.
Date: March 18, 1947
Creator: Coleman, Robert P. & Stempin, Carl W.
Item Type: Refine your search to only Report
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