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4,107 Matching Results
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Stress Rupture of Heat Resisting Alloys as a Rate Process
Note presenting the application of the equations of the theory of rate processes to stress rupture in order to predict the experimental stress and temperature dependence of the time for rupture for three heat-resisting alloys. Results regarding stress dependence, temperature dependence of slope factor, and temperature dependence of apparent free energy of activation are provided.
Date:
September 1946
Creator:
Machlin, E. S. & Nowick, A. S.
System:
The UNT Digital Library
Strain-Gage Study of Internally Cooled Exhaust Valves Having Various Throat Designs
Note presenting three internally cooled exhaust valves with the same external dimensions but different throat designs were investigated to determine a method of obtaining increased coolant-flow area with increasing stresses. The valves were statistically loaded to simulate stresses in the throat region caused by valve closure.
Date:
August 1946
Creator:
Holms, Arthur G. & Faldetta, Richard D.
System:
The UNT Digital Library
Flight Measurements of the Lateral Control Characteristics of Narrow-Chord Ailerons on the Trailing Edge of a Full-Span Slotted Flap
Note presenting results of flight tests made to determine the effect of flap deflection on the lateral control characteristics of a modified Brewster F2A-2 airplane equipped with partial-span narrow-chord ailerons on the trailing edge of a full-span NACA slotted flap. The results indicated that the effectiveness of the ailerons was greatly reduced at flap deflections greater than about 20 degrees.
Date:
February 1947
Creator:
Sawyer, Richard H.
System:
The UNT Digital Library
A Comparison of the Lateral Motion Calculated for Tailless and Conventional Airplanes
Theoretical analysts of lateral dynamic motion of tailless and conventional airplanes was made for fighter and heavy transport. Their reactions to a lateral gust and control power required by each for simple maneuvers were determined and compared. Both types of airplanes require almost identical aileron control power to perform a given maneuver; tailless airplane requires about 1-2 to 1-3 directional control power of conventional airplane. Tailless airplane also shows greatest displacement for a given disturbance and has least damping in oscillatory mode.
Date:
February 1947
Creator:
Harper, Charles W. & Jones, Arthur L.
System:
The UNT Digital Library
Two-dimensional wind-tunnel investigation of a 10.7-percent-thick symmetrical tail section with a 0.40 airfoil-chord control surface and a 0.20 control-surface-chord tab
Report presenting an investigation of a 10.7-percent-thick symmetrical tail section equipped with a flat-side airfoil-chord flap with a flap-chord overhang and a plain flap-chord tab. Airfoil lift, drag, pitching-moment, and flap and tab hinge-moment characteristics were determined at various flap and tab deflections.
Date:
June 1947
Creator:
Braslow, Albert L.
System:
The UNT Digital Library
Tentative Tables for the Properties of the Upper Atmosphere
Note presenting three temperature-height relationships and one composition-height relationship developed by the NACA and tables based on them for pertinent properties of the upper atmosphere. Two sets of tables based on the adopted tentative standard specifications for the upper atmosphere are presented.
Date:
January 1947
Creator:
Warfield, Calvin N.
System:
The UNT Digital Library
Effects of Partial Admission on Performance of a Gas Turbine
Report presenting an investigation of the effect of partial admission of the driving fluid on the performance of a representative full-admission, production-type gas turbine. Results regarding losses, full-admission performance, partial-admission performance, partial admission as a means of power control, and a comparison of partial admission with other methods of power control are provided.
Date:
February 1949
Creator:
Kohl, Robert C.; Herzig, Howard Z. & Whitney, Warren J.
System:
The UNT Digital Library
Method for Evaluating From Shadow or Schlieren Photographs the Pressure Drag in Two-Dimensional or Axially Symmetrical Flow Phenomena With Detached Shock
"A method has been developed for evaluating from shadow or schileren photographs the pressure drag of axially symmetrical bodies at zero angle of attack or of two-dimensional bodies producing detached shock. The method consists in the determination of the flow properties along a characteristic line and the application of the momentum theorem to a stream tube around the body. The method can be applied to the determination of external drag of supersonic inlets with subsonic flow at the entrance of the inlet" (p. 1).
Date:
February 1949
Creator:
Ferri, Antonio
System:
The UNT Digital Library
Experimental Investigation of the Stress Distribution Around Reinforced Circular Cut-Outs in Skin Stringer Panels Under Axial Loads
Note presenting results of strain surveys around four reinforced circular cut-outs successively made in an axially loaded skin-stringer tension panel. Curves are presented which show the distribution of stringer and shear stresses in the panel and bending stresses in the reinforcing rings.
Date:
March 1947
Creator:
Farb, Daniel
System:
The UNT Digital Library
Comparison between predicted and observed performance of gas-turbine stator blade designed for free-vortex flow
Report presenting a comparison between the calculated design performance of a gas-turbine stator blade and its performance in a sector of an annular cascade tunnel. The gas velocities on the blade surface were computed by the stress filament method and compared with experimental values, with which they agreed satisfactorily. Results regarding discharge angle, vane-surface-velocity distribution, tangential- and axial-velocity distribution, and radial-equilibrium consideration are provided.
Date:
April 1949
Creator:
Huppert, M. C. & MacGregor, Charles
System:
The UNT Digital Library
The application of airfoil studies to helicopter rotor design
From Summary: "In order to facilitate the application of miscellaneous airfoil data to the problems of the helicopter designer, a discussion of a number of the problems most frequently arising is presented. A reference list of published papers on airfoil section characteristics (or their application) which experience has shown to be useful in connection with these helicopter problems is included."
Date:
February 1949
Creator:
Gustafson, F. B.
System:
The UNT Digital Library
The Synthesis and Purification of Aromatic Hydrocarbons 2: 1, 2, 4-Trimethylbenzene
Note presenting a new method for the synthesis and purification of a 14-gallon quantity of 1,2,4-trimethylbenzene. The method consists in the chloromethylation of m- and p-xylenes, subsequent formation of ethyl dimethylbenzyl ethers, and hydrogenolysis of the ethers to yield the hydrocarbon. Results regarding chloromethylation of xylene, conversion of dimethylbenzyl chlorides to ethyl dimethylbenzyl ethers, hydrogenolysis of the ethyl dimethylbenzyl ethers, and identification of biproducts are provided.
Date:
January 1946
Creator:
Ebersole, Earl R.
System:
The UNT Digital Library
A study of flow changes associated with airfoil section drag rise at supercritical speeds
Report presenting a study of experimental pressure distributions and section characteristics for several moderately thick airfoil sections were made. The pressure distributions and section force characteristics of several moderately thick airfoil sections at Mach numbers above the drag-divergence Mach numbers were analyzed.
Date:
February 1949
Creator:
Nitzberg, Gerald E. & Crandall, Stewart
System:
The UNT Digital Library
An analysis of the factors that affect the exhaust process of a four-stroke-cycle reciprocating engine
From Introduction: "An investigation was made to determine the relative significance of the factors that affect the exhaust process; the effects that an exhaust-process change has on cylinder charging were given special attention. Differential equations of this nature have been developed by Kemble (reference 1) but the forms of these equations are such that general conclusions regarding the various factors affecting the exhaust process cannot be determined."
Date:
April 1947
Creator:
Stanitz, John D.
System:
The UNT Digital Library
Effects of Several Design Variables on Turbine-Wheel Weight
Report presenting an analysis showing the effect of several design variables on turbine-wheel flight. Equations are developed for the calculations of weights of the disk, the rim, and the blades, and use the following variables: the blading aspect ratio and solidity, the ratio of the centrifugal stress at the blade roots to that in the disk, and the ratio of wheel diameter at the blade root to wheel diameter at the blade tip.
Date:
February 1949
Creator:
LaValle, Vincent L. & Huppert, Merle C.
System:
The UNT Digital Library
Frequency-Response Method for Determination of Dynamic Stability Characteristics of Airplanes With Automatic Controls
Note presenting a frequency-response method for determining the critical control-gearing and hunting oscillations of airplanes with automatic pilots. The method is graphical and has several advantages over the standard numerical procedure based on Routh's discriminant. Several examples are worked out to illustrate the application of the frequency-response method in determining the effect of automatic-pilot lag or lead on critical control gearing and in determining the amplitude and frequency of hunting.
Date:
March 1947
Creator:
Greenberg, Harry
System:
The UNT Digital Library
Investigations of Free Turbulent Mixing
Note presenting a discussion of the integral relations for flow of the boundary-layer type. It is shown that the characteristic laws of spread of jets, wakes, and so forth, can be obtained directly for the laminar case and, with the help of dimensional reasoning, for the turbulent case as well. Measurements of the mean velocity, the intensity and scale of the turbulent fluctuations, and of the turbulent shear in a two-dimensional mixing zone are presented.
Date:
August 1947
Creator:
Liepmann, Hans Wolfgang & Laufer, John
System:
The UNT Digital Library
Performance of axial-flow fan and compressor blades designed for high loadings
Report presenting an investigation to determine the effects of loading on the performance of axial-flow fan and compressor blades in a test blower. Results regarding verification of the two-dimensional design data and effects of blade roughness are provided.
Date:
February 1947
Creator:
Bogdonoff, Seymour M. & Herrig, L. Joseph
System:
The UNT Digital Library
On Compressibility Corrections for Subsonic Flow Over Bodies of Revolution
"A study of the subsonic flow past an infinitely long corrugated circular cylinder is presented to show the relation between two-dimensional and axisymmetrical flow. In fact, a solution is obtained which contains as limiting cases both the Prandtl-Glauert correction for two-dimensional flow and the Göthert correction for flow past slender bodies of revolution. Included in the paper are velocity-correction formulas for a cylinder with a single bump and for a corrugated cylinder in the presence of walls" (p. 1).
Date:
February 1949
Creator:
Reissner, Eric
System:
The UNT Digital Library
Triangular wings cambered and twisted to support specified distributions of lift at supersonic speeds
Report presenting an application of the linearized supersonic flow theory to the calculation of the camber and twist required for various lift distributions on a triangular wing with leading edges behind the Mach cone. Several specific examples are used and plots of the cambered surfaces, corresponding lift distributions, and values of the theoretical drag coefficients are presented.
Date:
February 1949
Creator:
Baldwin, Barrett S., Jr.
System:
The UNT Digital Library
Experimental Verification of Two Methods for Computing the Take-Off Ground Run of Propeller-Driven Aircraft
Note presenting a comparison between the measured take-off ground run of an airplane equipped with seven different propeller-engine gear-ratio combinations and the computed distances by two different methods. Results indicated that the values of ground run calculated by Diehl's approximate method checked experimental values with 7 percent but were in error as much as 10 to 15 percent under certain conditions. Improved methods of thrust computation may be required in order to avoid large errors and before any more rigorous methods can be substituted for Diehl's method.
Date:
June 1947
Creator:
Gasich, Welko E.
System:
The UNT Digital Library
Turbosupercharger-Rotor Temperatures in Flight
Note presenting temperatures of a turbosupercharger rotor measured in flight for a variety of conditions by thermocouples, the leads of which were brought away from the turbine by means of rotating slip rings and stationary brushes. A consistent and almost linear relation was shown between turbine temperature at the outer edge of the rim and the effective exhaust-gas temperature at the surfaces of the blades on three successive flights at cruising power.
Date:
October 1946
Creator:
Bartoo, Edward R.
System:
The UNT Digital Library
Plastic buckling of simply supported compressed plates
Report presenting an investigation to ascertain the validity of various theories for the plastic buckling of compressed simply supported plates by means of local-instability tests of drawn square tubes of 14S-T6 aluminum alloy. The results obtained were in excellent agreement with Stowell's unified theory for the plastic buckling of columns and plates.
Date:
April 1949
Creator:
Pride, Richard A. & Heimerl, George J.
System:
The UNT Digital Library
Effect of Automatic Stabilization on the Lateral Oscillatory Stability of a Hypothetical Airplane at Supersonic Speeds
Note presenting an investigation to determine the effect of automatic stabilization on the lateral oscillatory stability of a hypothetical supersonic airplane. The investigation included an autopilot sensitive to either the yawing or rolling angular velocity. The results of the investigation indicated that all the automatic pilots improved the stability of the original unstable short-period oscillation.
Date:
March 1949
Creator:
Sternfield, Leonard
System:
The UNT Digital Library