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Rate of Heat Transfer From Finned Metal Surfaces

Description: The object was to evaluate the factors which control the rate of heat transfer to a moving current of air from finned metal surfaces similar to those used on aircraft engine cylinders. This was to establish data which will enable the finning of cooling surfaces to be designed to suit the particular needs of any specific application. Most of the work was done on flat copper specimens 6 inches square, upon which were mounted copper fins with spacings varying from 1/2 inch to 1/12 inch. All fins w… more
Date: January 1930
Creator: Taylor, C. Fayette & Rehbock, A.
Partner: UNT Libraries Government Documents Department
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Comparative Performance Obtained With XF7C-1 Airplane Using Several Different Engine Cowlings

Description: Discussed here are problems with the use of cowlings with radial air cooled engines. An XF7C-1 airplane, equipped with service cowling and with narrow ring, wide ring, and exhaust collector ring cowlings over the service cowling, was used. For these four cowling conditions, the rate of climb and high speed performance were determined, the cylinder conditions were measured, and pictures to show visibility were taken. The level flight performance obtained with an engine speed of 1900 r.p.m. for t… more
Date: February 1930
Creator: Schey, Oscar W.; Johnson, Ernest & Gough, Melvin N.
Partner: UNT Libraries Government Documents Department
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Injection Labs in a Common-Rail Fuel Injection System

Description: Note presenting injection lags determined for a common-rail fuel injection system for a compression-ignition engine. The system consisted of a high-pressure reservoir, a timing valve, an injection valve tube, and an automatic injection valve. Results regarding the variable injection valve tube length, variable tube diameter, variable valve opening pressure, variable injection pressure, and variable initial pressure are provided.
Date: February 1930
Creator: Rothrock, A. M.
Partner: UNT Libraries Government Documents Department
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Test of an Adjustable Pitch Model Propeller at Four Blade Settings

Description: "This note describes tests of an adjustable blade metal model propeller, both in a free wind stream and in combination with a model fuselage, at four settings of the blades. The model propeller is designed for a uniform nominal pitch/diameter ratio of .7 and the blade settings used correspond to nominal pitch/diameter ratios of .5, .7, .9, and 1.1 at the .6 radius. The tests show that propellers of this type may be considerably changed in setting from the designed pitch angles and yet give exce… more
Date: February 1930
Creator: Lesley, E. P.
Partner: UNT Libraries Government Documents Department
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The Effect of Wing Tip Floating Ailerons on the Autorotation of a Monoplane Wing Model

Description: "The preliminary tests described here were made to determine the extent to which wing tip floating ailerons might be effective in reducing airplane spinning tendencies. The tests showed that initial spinning tendencies and rates of stable spinning could doubtless be reduced by the use of tip floating ailerons on an airplane. It also appears to be desirable to reduce to a minimum the interference between wing and aileron. This would serve to maintain uniformity of action at all angles of attack … more
Date: March 1930
Creator: Knight, Montgomery & Wenzinger, Carl J.
Partner: UNT Libraries Government Documents Department
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The Structure and Properties of Parachute Cloths

Description: "The requisite properties of a parachute cloth are discussed and the methods for measuring these properties described. In addition to the structural analysis of the cloths, the properties measured were weight, breaking strength, tear resistance, elasticity, and air permeability. Thirty-six silk cloths of domestic manufacture, not previously used in parachute construction are compared with some silk cloths of foreign manufacture" (p. 1).
Date: March 1930
Creator: McNicholas, H. J. & Hedrick, A. F.
Partner: UNT Libraries Government Documents Department
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Pressure distribution on the tail surfaces of a PW-9 pursuit airplane in flight

Description: Presented here are pressure distribution data obtained from the tail surfaces of a PW-9 in a number of flight maneuvers. The results given are part of those obtained in an extensive investigation of the pressure distribution over all of the lifting and control surfaces of this airplane. The results are given in tabular and curve form and are discussed briefly with respect to their comparison with existing tail surface design specifications. It is recommended that tail load design loadings shoul… more
Date: April 1930
Creator: Rhode, Richard V.
Partner: UNT Libraries Government Documents Department
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Full Scale Drag Tests on Various Parts of Fairchild (FC-2W2) Cabin Monoplane

Description: "The drag due to the various parts of a Fairchild (FC-2W2) cabin monoplane was measured at air speeds varying from 50 to 100 m.p.h., in the Twenty-Foot Propeller Research Tunnel of the National Advisory Committee for Aeronautics. It was found that the largest drag was due to the radial air-cooled engine. The measured drag due to the landing gear was also large, being about 4/5 of that due to the engine" (p. 1).
Date: May 1930
Creator: Herrnstein, William H., Jr.
Partner: UNT Libraries Government Documents Department
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Refrigerated wind tunnel tests on surface coatings for preventing ice formation

Description: "This investigation was conducted to determine the effectiveness of various surface coatings as a means for preventing ice formations on aircraft in flight. The substances used as coatings for these tests are divided into two groups: compounds soluble in water, and those which are insoluble in water. It was found that certain soluble compounds were apparently effective in preventing the formation of ice on an airfoil model, while all insoluble compounds which were tested were found to be ineffe… more
Date: May 1930
Creator: Knight, Montgomery & Clay, William C.
Partner: UNT Libraries Government Documents Department
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Some effects of air and fuel oil temperatures on spray penetration and dispersion

Description: Presented here are experimental results obtained from a brief investigation of the appearance, penetration, and dispersion of oil sprays injected into a chamber of highly heated air at atmospheric pressure. The development of single sprays injected into a chamber containing air at room temperature and at high temperature was recorded by spray photography equipment. A comparison of spray records showed that with the air at the higher temperature, the spray assumed the appearance of thin, transpa… more
Date: May 1930
Creator: Gelalles, A. G.
Partner: UNT Libraries Government Documents Department
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Calibration and lag of a Friez type cup anemometer

Description: "Tests on a Friez type cup anemometer have been made in the variable density wind tunnel of the Langley Memorial Aeronautical Laboratory to calibrate the instrument and to determine its suitability for velocity measurements of wind gusts. The instrument was calibrated against a Pitot-static tube placed directly above the anemometer at air densities corresponding to sea level, and to an altitude of approximately 6000 feet. Air-speed acceleration tests were made to determine the lag in the instru… more
Date: June 1930
Creator: Pinkerton, Robert M.
Partner: UNT Libraries Government Documents Department
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Identification of Aircraft Tubing by Rockwell Test

Description: A large number of tests were made on tubes of 1025 and 4130X steel, in various diameters and wall thicknesses, and after diverse heat treatments. The Rockwell B scale was employed, as being the best suited to the ranges of hardness encountered. Only satisfactory chrome molybdenum tubes were found to show a hardness in excess of 90-B after normalizing.
Date: June 1930
Creator: Knerr, Horace
Partner: UNT Libraries Government Documents Department
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Identification of Aircraft Tubing by Rockwell Test

Description: Seamless steel tubing is today the principal material of construction for aircraft. The commercial grade of tubing containing about 0.10 to 0.20% carbon at first used is being superseded by two grades which are approved by the army and navy, and which are also becoming standard for commercial airplanes.
Date: June 1930
Creator: Knerr, Horace
Partner: UNT Libraries Government Documents Department
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Performance of a high-speed compression-ignition engine using multiple orifice fuel injection nozzles

Description: This report presents test results obtained at the Langley Memorial Aeronautical Laboratory of the National Advisory Committee for Aeronautics during an investigation to determine the relative performance of a single-cylinder, high-speed, compression-ignition engine when using fuel injection valve nozzles with different numbers, sizes, and directions of round orifices. A spring-loaded, automatic injection valve was used, centrally located at the top of a vertical disk-type combustion chamber for… more
Date: June 1930
Creator: Spanogle, J. A. & Foster, H. H.
Partner: UNT Libraries Government Documents Department
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Strength in Shear of the Thin Curved Sheets of Alclad

Description: "This note is on an investigation made to obtain information on the strength of thin curved sheets of Alclad in shear. Designers may utilize this material as a strength member as well as for a covering for the wings and fuselages. A reduction may then be made in the size of the internal strength members. These experiments were undertaken with the object of securing the maximum value from the metal in this respect" (p. 1).
Date: June 1930
Creator: Smith, George Michael
Partner: UNT Libraries Government Documents Department
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The Prevention of the Ice Hazard on Airplanes

Description: A review of various methods to prevent ice formation and adhesion to aircraft surfaces is given. It was concluded that the adhesion of ice to a surface may be reduced somewhat by the application of certain waxes and varnishes. In the experiments described, the varnishes containing calcium stearate and calcium oleate gave the best results. In wind tunnel tests, the adhesion was further reduced by the application of these waxes and varnishes to a thin, heat insulating layer of rubber.
Date: July 1930
Creator: Geer, William C. & Scott, Merit
Partner: UNT Libraries Government Documents Department
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Span load distribution on two monoplanes wing models as affected by twist and sweepback

Description: The results presented in this note show the effect of twist and sweepback on the span load distribution over two monoplane wing models. The tests were made in the Atmospheric Wind Tunnel of the Langley Memorial Aeronautical Laboratory. The data are taken from the results of an investigation dealing primarily with lateral stability. As presented, they are suitable as an aid in the structural design of certain monoplane wings.
Date: July 1930
Creator: Knight, Montgomery & Noyes, Richard W.
Partner: UNT Libraries Government Documents Department
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Pressure distribution over a Douglas wing tip on a biplane in flight

Description: "This note presents the results obtained in pressure distribution tests on the right upper wing panel and tip of a Douglas M-3 airplane in flight. These tests are a part of a more extensive investigation of the effect of changes in tip shape on the load distribution, the tip reported herein being the first of a series of tip shapes being tested. The results are given in tables and curves in such form that the load distribution for any conditions may be determined easily. Tests were made at Lang… more
Date: August 1930
Creator: Rhode, Richard V. & Lundquist, Eugene E.
Partner: UNT Libraries Government Documents Department
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Alterations and Tests of The "Farnboro" Engine Indicator

Description: "The 'Farnboro' electric indicator was tested as received from the manufacturers, and modifications made to the instrument to improve its operation. The original design of disk valve was altered so as to reduce the mass, travel, and seat area. Changes were made to the recording mechanism, which included a new method of locating the top center position on the record. The effect of friction on the motion of the pointer while taking motoring and power cards was eliminated by providing a means of p… more
Date: September 1930
Creator: Collins, John H., Jr.
Partner: UNT Libraries Government Documents Department
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An Investigation of Airplane Landing Speeds

Description: "This paper describes an investigation on airplane landing speeds which was made to determine the applicability of accepted aerodynamic theory to the prediction of this particular performance characteristic. The experimental work consisted in measuring the landing speed of several monoplanes by a new photographic method. The results of these tests supplemented by available information regarding biplanes were compared with predictions made with basic aerodynamic theory" (p. 1).
Date: September 1930
Creator: Ridley, Kenneth F.
Partner: UNT Libraries Government Documents Department
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An Accurate Method of Measuring the Moments of Inertia of Airplanes

Description: From Summary: "This note contains a description of an improved apparatus and procedure used by the NACA for determining the moments of inertia of airplanes. The method used, based on the pendulum theory, is similar to that previously used, but a recent investigation of its accuracy has resulted in the improvements described herein. The error, when using the new apparatus and procedure, has been found to be of the order of 1 per cent."
Date: October 1930
Creator: Miller, M. P.
Partner: UNT Libraries Government Documents Department
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Analytical Determination of the Load on a Trailing Edge Flap

Description: From Summary: "This report presents a theoretical analysis of the lift on a trailing edge flap. An analytical expression has been derived which enables the computation of the flap load coefficient. The theoretical results seem to show a fair agreement with the meager experimental results which are available."
Date: October 1930
Creator: Pinkerton, Robert M.
Partner: UNT Libraries Government Documents Department
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Effect of Orifice Length-Diameter Ratio on Spray Characteristics

Description: "The effect of variations of orifice length to diameter ratio on spray characteristics was determined for a 0.014-inch and a 0.040-inch orifice for ratio of 0.5 to 4.0. The nozzles containing the orifices were mounted in an injection valve and tested with a plan stem and with a helically grooved stem. The injection pressure was varied from 4000 to 8000 pounds per square inch. The air density into which the fuel was sprayed was varied from the density obtained with a pressure of 60 pounds per sq… more
Date: October 1930
Creator: Gelalles, A. G.
Partner: UNT Libraries Government Documents Department
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Methods for the Identification of Aircraft Tubing of Plain Carbon Steel and Chromium-Molybdenum Steel

Description: The survey of the possibilities for distinguishing between plain carbon and chromium-molybdenum steel tubing included the Herbert pendulum hardness, magnetic, sparks, and chemical tests. The Herbert pendulum test has the disadvantages of all hardness tests in being limited to factory use and being applicable only to scale-free, normalized material. The small difference in the range of hardness values between plain carbon and chromium-molybdenum steels is likewise a disadvantage.
Date: October 1930
Creator: Mutchler, W. H. & Buzzard, R. W.
Partner: UNT Libraries Government Documents Department
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