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Stopping Methods and Costs

Description: Report presenting a study of stoping methods and costs and summarizing the data obtained in earlier publications and those obtained during investigations in the field that apply particularly to stoping.
Date: 1936
Creator: Jackson, Charles Freeman & Gardner, E. D.
Partner: UNT Libraries Government Documents Department

Report of the Twenty-Fifth National Conference on Weights and Measures, 1935

Description: Report of the annual conference on weights and measures, hosted by the U.S. National Bureau of Standards in Washington D.C. It includes conference proceedings, a list of attendees, information about committees and officers, and other reports or commentaries discussed at the meetings.
Date: June 1936
Creator: United States. Bureau of Standards.
Partner: UNT Libraries Government Documents Department

Disposal of Oil-Field Brines in the Arkansas River Drainage Area in Western Kansas

Description: Report issued by the U.S. Bureau of Mines on the disposal methods of oil-field brine. The study focuses on the Arkansas River area of western Kansas. This report includes tables, graphs, illustrations, and maps.
Date: October 1936
Creator: Wilhelm, C. J.; Thorne, H. M. & Pryor, M. F.
Partner: UNT Libraries Government Documents Department

Progress Reports - Metallurgical Division: 13. Electrometallurgical Investigations

Description: Report issued by the U.S. Bureau of Mines on the progress made on projects in the Metallurgical Division. Descriptions of progress in the different projects and operations conducted are listed. This report includes tables, graphs, and illustrations.
Date: October 1936
Creator: Koster, J.; Shelton, S. M. & Knickerbocker, R. G.
Partner: UNT Libraries Government Documents Department

Permissible Electric Mine Lamps (Supplement to Bulletin 332)

Description: Report issued by the U.S. Bureau of Mines on the improvements made on permissible electric mine lamps. The types of electric lamps approved for use, and their characteristics are presented. This report includes tables.
Date: June 1936
Creator: Ilsley, L. C. & Hooker, A. B.
Partner: UNT Libraries Government Documents Department

United States Earthquakes, 1936

Description: Report discussing earthquake activity in the United States during 1936. The report is broken down by regions and has sections for specific earthquakes.
Date: 1936
Partner: UNT Libraries Government Documents Department

General instability criterion of laminar velocity distributions

Description: The present paper describes the results of a stability investigation on symmetrical velocity profiles in a channel and of boundary-layer profiles. The effect of friction was assumed to be vanishing and did not occur in the stability consideration so far as it had been resorted to for preparatory asymptotic considerations. Proceeding on very general premises as regards the form of the velocity distribution, a proof was deduced of the elementary theorem that velocity profiles with inflection points are unstable.
Date: April 1936
Creator: Tollmien, W.
Partner: UNT Libraries Government Documents Department

Behavior of Turbulent Boundary Layers on Curved Convex Walls

Description: The system of linear differential equations which indicated the approach of separation and the so-called "boundary-layer thickness" by Gruschwitz is extended in this report to include the case where the friction layer is subject to centrifugal forces. Evaluation of the data yields a strong functional dependence of the momentum change and wall drag on the boundary-layer thickness radius of curvature ratio for the wall. It is further shown that the transition from laminar to turbulent flow occurs at somewhat higher Reynolds Numbers at the convex wall than at the flat plate, due to the stabilizing effect of the centrifugal forces.
Date: April 1936
Creator: Schmidbauer, Hans
Partner: UNT Libraries Government Documents Department

Turbulent Jet Expansion

Description: This report was made to study the velocity distribution in an open, in a partially open, and in a partially expanding jet. The open-jet observations reveal minor systematic discrepancies from Tollmien's theoretical velocity distribution. The shearing-stress distribution for the partially open jet was determined. The value derived for the ratio of mixing distance to jet width was found to be in close agreement with the corresponding value for the open-jet boundary.
Date: March 1936
Creator: Förthmann, E.
Partner: UNT Libraries Government Documents Department

The Formation of Ice on Airplanes

Description: "The present report examines the problem of ice formation from the point of view of the pilot and the meteorologist. Their experiences prove the ice deposit to be first and foremost a navigational problem and only secondarily a question of de-icing devices. With correct utilization of the meteorological information by the flyer, ice hazard can in many cases be minimized or avoided. Ice formation and the different types of ice deposits are listed and discussed" (p. 1).
Date: February 1936
Creator: Noth, H. & Polte, W.
Partner: UNT Libraries Government Documents Department

Methods and Formulas for Calculating the Strength of Plate and Shell Constructions as Used in Airplane Design

Description: "This report is a compilation of previously published articles on formulas and methods of calculation for the determination of the strength and stability of plate and shell construction as employed in airplane design. In particular, it treats the problem of isotropic, orthotopic, and stiffened rectangular plates, thin curved panels, and circular cylinders under various loading conditions. The purpose of appending the pertinent literature references following the subjects discussed was to facilitate a comprehensive study of the treated problems" (p. 1).
Date: February 1936
Creator: Heck, O. S. & Ebner, H.
Partner: UNT Libraries Government Documents Department

Torsion and buckling of open sections

Description: Following an abstract of the well-known theory of torsion in compression, the writers give directions for the practical calculation of the values of C(sub BT) (resistance to flexure and torsion) and i(sub SP(exp 2)), which determine the torsion. The second part treats the experiments in support of the theory of torsion of plain and flanged angle sections.
Date: January 1936
Creator: Wagner, H. & Pretschner, W.
Partner: UNT Libraries Government Documents Department

Status of Wing Flutter

Description: "This report presents a survey of previous theoretical and experimental investigations on wing flutter covering thirteen cases of flutter observed on airplanes. The direct cause of flutter is, in the majority of cases, attributable to (mass-) unbalanced ailerons. Under the conservative assumption that the flutter with the phase angle most favorable for excitation occurs only in two degrees of freedom, the lowest critical speed can be estimated from the data obtained on the oscillation bench" (p. 1).
Date: January 1936
Creator: Küssner, H. G.
Partner: UNT Libraries Government Documents Department

An Approximate Spin Design Criterion for Monoplanes

Description: "An approximate empirical criterion, based on the projected side area and the mass distribution of the airplane, was formulated. The British results were analyzed and applied to American designs. A simpler design criterion, based solely on the type and the dimensions of the tail, was developed; it is useful in a rapid estimation of whether a new design is likely to comply with the minimum requirements for safety in spinning" (p. 1).
Date: June 1936
Creator: Seidman, Oscar & Donlan, Charles J.
Partner: UNT Libraries Government Documents Department

A general tank test of a model of the hull of the British Singapore IIC flying boat

Description: A general test was made in the N.A.C.A. tank of a 1/12-size model of the hull of the British Singapore IIC flying boat loaned by the Director of Research, British Air Ministry. The results are given in charts and are compared with the results of tests of a model of an American flying-boat hull, the Sikorsky S-40. The Singapore hull has a greater hump resistance but a much lower high-speed resistance than the S-40.
Date: September 1936
Creator: Dawson, John R. & Truscott, Starr
Partner: UNT Libraries Government Documents Department

Limitations of the Pilot in Applying Forces to Airplane Controls

Description: Measurements were made to determine the relative maximum forces a pilot can exert on the controls of an airplane with the view of obtaining systematic data upon which to base the location of controls within the cockpit and the design of the control surfaces. A cockpit model of generous proportions, capable of being rotated to any attitude, was built with the location of the control stick and rudder pedals adjustable over a wide range of positions with respect to the seat. Besides measurements of maximum forces obtainable with various control locations and with the pilot in several attitudes, estimates of forces within the range normally encountered in flight were made to gain an indication of the accuracy of estimating control forces.
Date: January 1936
Creator: Gough, M. N. & Beard, A. P.
Partner: UNT Libraries Government Documents Department

A study of autogiro rotor-blade oscillations in the plane of the rotor disk

Description: An analysis of the factors governing the oscillation of an autogiro rotor blade in the plane of the rotor disk showed that the contribution of the air forces to the resultant motion was small and that the oscillation is essentially a direct effect of the rotor-blade flapping motion. A comparison of calculated oscillations with those measured in flight on three different rotors disclosed that the calculations gave satisfactory agreement with experiment. The calculated air forces on the rotor blade appear to be larger than the experimental ones, but this discrepancy can be attributed to the deficiencies in the strip analysis.
Date: September 1936
Creator: Wheatley, John B.
Partner: UNT Libraries Government Documents Department

Tank tests of three models of flying-boat hulls of the pointed-step type with different angles of dead rise - NACA model 35 series

Description: From Summary: "The results of tank tests of three models of flying-boat hulls of the pointed-step type with different angles of dead rise are given in charts and are compared with results from tests of more conventional hulls. Increasing the angle of dead rise from 15 to 25 degrees: had little effect on the hump resistance; increased the resistance throughout the planning range; increased the best trim angle; reduced the maximum positive trimming moment required to obtain best trim angle; and had but a slight effect on the spray characteristics. For approximately the same angles of dead rise the resistance of the pointed-step hulls were considerably lower at high speeds than those of the more conventional hulls."
Date: January 1936
Creator: Dawson, John R.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Tests of Wing Flaps Suitable for Direct Control of Glide-Path Angle

Description: "Preliminary tests have been made for the purpose of obtaining a flap arrangement suitable for direct and immediate control of the steepness of the glide path of an airplane, a use for which present flaps are not satisfactory. An attempt has been made to develop a flap giving a reasonably high maximum lift coefficient with relatively low deflection and maintaining this value of the maximum lift coefficient with a large increase of deflection, the increase in deflection being accompanied by a large increase in drag. An arrangement was found that gave a maximum lift coefficient of approximately 1.90 for all flap deflections between 25 and 80 degrees, within which range the drag of the wing increased regularly to a large value" (p. 1).
Date: January 1936
Creator: Weick, Fred E.
Partner: UNT Libraries Government Documents Department

Effect of Several Factors on the Cooling of a Radial Engine in Flight

Description: "Flight tests of a Grumman Scout (XSF-2) airplane fitted with a Pratt & Whitney 1535 supercharged engine were conducted to determine the effect of engine power, mass flow of the cooling air, and atmospheric temperature on cylinder temperature. The tests indicated that the difference in temperature between the cylinder wall and the cooling air varied as the 0.38 power of the brake horsepower for a constant mass flow of cooling air, cooling-air temperature, engine speed, and brake fuel consumption. The difference in temperature was also found to vary inversely as the 0.39 power of the mass flow for points on the head and the 0.35 power for points on the barrel, provided that engine power, engine speed, brake fuel consumption, and cooling-air temperature were kept constant" (p. 1).
Date: November 1936
Creator: Schey, Oscar W. & Pinkel, Benjamin
Partner: UNT Libraries Government Documents Department
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