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  Partner: UNT Libraries Government Documents Department
 Decade: 1940-1949
 Year: 1942
 Collection: Technical Report Archive and Image Library
Bending with large deflection of a clamped rectangular plate with length-width ratio of 1.5 under normal pressure

Bending with large deflection of a clamped rectangular plate with length-width ratio of 1.5 under normal pressure

Date: April 14, 1942
Creator: Levy, Samuel & Greenman, Samuel
Description: The Von Karman equations for a thin flat plate with large deflections are solved for the special case of a plate with clamped edges having a ratio of length to width of 1.5 and loaded by uniform normal pressure. Center deflections, membrane stresses, and extreme-fiber bending stresses are given as a function of pressure for center deflections up to twice the thickness of the plate. For small deflections the results coincide with those obtained by Hencky from the linear theory. The maximum stresses and center deflection at high pressures differ less than 3 percent from those derived by Bostnov for an infinitely long plate with clamped edges. This agreement suggests that clamped plates with a length-to-width ratio greater than 1.5 may be reared as infinitely long plates for purposes of design.
Contributing Partner: UNT Libraries Government Documents Department
A Brief Study of the Speed Reduction of Overtaking Airplanes by Means of Air Brakes, Special Report

A Brief Study of the Speed Reduction of Overtaking Airplanes by Means of Air Brakes, Special Report

Date: May 1, 1942
Creator: Pearson, H. A. & Amderspm. R. F.
Description: As an aid to airplane designers interested in providing pursuit airplanes with decelerating devices intended to increase the firing time when overtaking another airplane, formulas are given relating the pertinent distances and speeds in horizontal flight to the drag increase required. Charts are given for a representative parasite-drag coefficient from which the drag increase, the time gained, and the closing distance may be found. The charts are made up for three values of the ratio of the final speed of the pursuing airplane to the speed of the pursued airplane and for several values of the ratio of the speed of the pursued airplane to the initial speed of the pursuing airplane. Charts are also given indicating the drag increases obtainable with double split flaps and with conventional propellers. The use of the charts is illustrated by an example in which it is indicated that either double split flaps or, under certain ideal conditions, reversible propellers should provide the speed reductions required.
Contributing Partner: UNT Libraries Government Documents Department
Calculated effects of full-span slotted and Fowler flaps on longitudinal stability and control characteristics for a typical fighter-type airplane with various tail modifications

Calculated effects of full-span slotted and Fowler flaps on longitudinal stability and control characteristics for a typical fighter-type airplane with various tail modifications

Date: July 1, 1942
Creator: Goranson, R Fabian
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Calculation of tab characteristics for flight conditions from wind-tunnel data

Calculation of tab characteristics for flight conditions from wind-tunnel data

Date: April 1, 1942
Creator: Sears, Richard I
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Calibration of three temperature probes and a pressure probe at high speeds

Calibration of three temperature probes and a pressure probe at high speeds

Date: April 1, 1942
Creator: Lindsey, W F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Calibrations of pitot-static tubes at high speeds

Calibrations of pitot-static tubes at high speeds

Date: July 1, 1942
Creator: Hensley, Reece V
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Characteristics of beveled-trailing-edge elevators on a typical pursuit fuselage at altitudes simulating-normal flight and spin conditions

Characteristics of beveled-trailing-edge elevators on a typical pursuit fuselage at altitudes simulating-normal flight and spin conditions

Date: December 1, 1942
Creator: Gillis, Clarence L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Characteristics of plain and balanced elevators on a typical pursuit fuselage at attitudes simulating normal-flight and spin conditions

Characteristics of plain and balanced elevators on a typical pursuit fuselage at attitudes simulating normal-flight and spin conditions

Date: March 1, 1942
Creator: Hoggard, H Page, Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Characteristics of Two Model Six-Blade Counterrotating Pusher Propellers of Conventional and Improved Aerodynamic Design

The Characteristics of Two Model Six-Blade Counterrotating Pusher Propellers of Conventional and Improved Aerodynamic Design

Date: April 1, 1942
Creator: Pepper, Edward & McHugh, James G.
Description: Two airfoil plans were used for propeller blades. One is modified Clark Y section designed for structural reliability and the second an NACA 16 airfoil section designed to produce minimum aerodynamic losses. At low air speeds, the propeller designed for aerodynamic effects showed a gain of from 1.5 to 4.0 percent in propulsive efficiency over the conventional type depending on the pitch. Because of the numerous variables involved, the effect of each one on the aerodynamic characteristics of the propellers could not be isolated.
Contributing Partner: UNT Libraries Government Documents Department
Coal-Mine Accidents in the United States, 1939

Coal-Mine Accidents in the United States, 1939

Date: 1942
Creator: Adams, William W.; Geyer, L. E. & Parry, M. G.
Description: Report compiled by the U.S. Bureau of Mines including statistics on fatal and non-fatal accidents in coal mines located in the United States as well as data regarding the various operations (e.g., number of miners employed and average production). The information is organized into tables for comparison and the text draws some overall conclusions in the summary.
Contributing Partner: UNT Libraries Government Documents Department
Coal-Mine Accidents in the United States, 1940

Coal-Mine Accidents in the United States, 1940

Date: 1942
Creator: Adams, William W.; Geyer, L. E. & Parry, M. G.
Description: Report compiled by the U.S. Bureau of Mines including statistics on fatal and non-fatal accidents in coal mines located in the United States as well as data regarding the various operations (e.g., number of miners employed and average production). The information is organized into tables for comparison and the text draws some overall conclusions in the summary.
Contributing Partner: UNT Libraries Government Documents Department
Column strength of magnesium alloy AM-57S

Column strength of magnesium alloy AM-57S

Date: July 1, 1942
Creator: Holt, M
Description: Tests were made to determine the column strength of extruded magnesium alloy AM-57S. Column specimens were tested with round ends and with flat ends. It was found that the compressive properties should be used in computations for column strengths rather than the tensile properties because the compressive yield strength was approximately one-half the tensile yield strength. A formula for the column strength of magnesium alloy AM-57S is given.
Contributing Partner: UNT Libraries Government Documents Department
Comparison of Intercooler Characteristics

Comparison of Intercooler Characteristics

Date: November 1, 1942
Creator: Valerino, Michael F
Description: No abstract available.
Contributing Partner: UNT Libraries Government Documents Department
A comparison of the results from general tank tests of 1/6- and 1/12-full-size models of the British Singapore IIC flying boat

A comparison of the results from general tank tests of 1/6- and 1/12-full-size models of the British Singapore IIC flying boat

Date: August 1, 1942
Creator: Truscott, Starr & Dawson, John R
Description: A 1/6-full-size model of the hull of the British Singapore IIC flying boat was tested in the NACA tank. The results are given in the form of charts and are compared with the results of previous tests made in the NACA tank of a 1/12-full-size model, published in NACA T.N. No. 580, and with the results of tests made in the British R.A.E. tank of another 1/6-full-size model of the same hull. When the data from the tests of the 1/6- and 1/12-full-size models were compared on the basis of Froude's law of comparison, differences were found. This fact supported the belief that the small scale of the model and the use of a model that was too small to suit the equipment of the NACA tank had caused the results of the tests of the 1/12-full-size model to be less reliable than the results of the tests of the 1/6-full-size model. The results of the tests of the two models agreed sufficiently well to show that test of a small model, if made meticulously and with suitable equipment, may give useable results, but that a larger model should be used whenever feasible. The results of the NACA tests of ...
Contributing Partner: UNT Libraries Government Documents Department
Comparison of tightness of 78 degrees machine-countersunk rivets driven in holes prepared with 78 degrees and 82 degrees countersinking tools

Comparison of tightness of 78 degrees machine-countersunk rivets driven in holes prepared with 78 degrees and 82 degrees countersinking tools

Date: September 1, 1942
Creator: Mandel, Merven W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Compressible Potential Flow Past Elliptic Symmetrical Cylinders at Zero Angle of Attack and with No Circulation

The Compressible Potential Flow Past Elliptic Symmetrical Cylinders at Zero Angle of Attack and with No Circulation

Date: October 1, 1942
Creator: Hantzsche, W. & Wendt, H.
Description: For the tunnel corrections of compressible flows those profiles are of interest for which at least the second approximation of the Janzen-Rayleigh method can be applied in closed form. One such case is presented by certain elliptical symmetrical cylinders located in the center of a tunnel with fixed walls and whose maximum velocity, incompressible, is twice the velocity of flow. In the numerical solution the maximum velocity at the profile and the tunnel wall as well as the entry of sonic velocity is computed. The velocity distribution past the contour and in the minimum cross section at various Mach numbers is illustrated on a worked out-example.
Contributing Partner: UNT Libraries Government Documents Department
Condensation trails : where they occur and what can be done about them

Condensation trails : where they occur and what can be done about them

Date: September 1, 1942
Creator: Pearson, H A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Construction of finned aluminum muffs for aircraft engine cylinder barrels

Construction of finned aluminum muffs for aircraft engine cylinder barrels

Date: April 1, 1942
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Contribution to the Design of Plywood Shells

Contribution to the Design of Plywood Shells

Date: October 1, 1942
Creator: Blumrich, S.
Description: The writer sets out to prove by calculation and experiment that by extensive utilization of the skin to carry axial load (reduction of stringer spacing) the stringer sections can be made small enough to afford a substantial saving in structural weight. This saving ranges from 5 to about 40 percent.
Contributing Partner: UNT Libraries Government Documents Department
Contribution to the ideal efficiency of screw propellers

Contribution to the ideal efficiency of screw propellers

Date: January 1, 1942
Creator: Hoff, Wilhelm
Description: The stipulation of best thrust distribution is applied to the annular elements of the screw propeller with infinitely many blades in frictionless, incompressible flow and an ideal jet propulsion system derived possessing hyperbolic angular velocity distribution along the blade radius and combining the advantage of uniform thrust distribution over the section with minimum slipstream and rotation losses. This system is then compared with a propeller possessing the same angular velocity at all blade elements and the best possible thrust distribution secured by means of an induced efficiency varying uniformly over the radius. Lastly, the case of the lightly loaded propeller also is discussed.
Contributing Partner: UNT Libraries Government Documents Department
Control-motion studies of the PBM-3 flying boat in abrupt pull-ups

Control-motion studies of the PBM-3 flying boat in abrupt pull-ups

Date: November 1, 1942
Creator: Smull, Leland K
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Control of Torsional Vibrations by Pendulum Masses

Control of Torsional Vibrations by Pendulum Masses

Date: November 1, 1942
Creator: Stieglitz, Albert
Description: Various versions of pendulum masses have been developed abroad within the past few years by means of which resonant vibrations of rotating shafts can be eliminated at a given tuning. They are already successfully employed on radial engines in the form of pendulous counterweights. Compared with the commonly known torsional vibration dampers, the pendulum masses have the advantage of being structurally very simple, requiring no internal damping and being capable of completely eliminating certain vibrations. Unexplained, so far, remains the problem of behavior of pendulum masses in other critical zones to which they are not tuned, their dynamic behavior at some tuning other than in resonance, and their effect within a compound vibration system and at simultaneous application of several differently tuned pendulous masses. These problems are analyzed in the present report. The results constitute an enlargement of the scope of application of pendulum masses, especially for in-line engines. Among other things it is found that the natural frequency of a system can be raised by means of a correspondingly tuned pendulum mass. The formulas necessary for the design of any practical version are developed, and a pendulum mass having two different natural frequencies simultaneously is described.
Contributing Partner: UNT Libraries Government Documents Department
Cooling in cruising flight with low fuel-air ratios

Cooling in cruising flight with low fuel-air ratios

Date: June 1, 1942
Creator: Wilson, Herbert A , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Cooling investigation of a B-24D engine-nacelle installation in the NACA full-scale tunnel

Cooling investigation of a B-24D engine-nacelle installation in the NACA full-scale tunnel

Date: November 1, 1942
Creator: Guryansky, Eugene R
Description: None
Contributing Partner: UNT Libraries Government Documents Department