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The N.A.C.A. Tank: A High-Speed Towing Basin for Testing Models of Seaplane Floats

Description: "This report describes the high-speed model towing basin of the National Advisory Committee for Aeronautics, usually referred to as the NACA Tank. The purpose of this piece of equipment is to enable the Committee to provide information and data regarding the performance of seaplanes on the water analogous to the information furnished concerning the performance of airplanes in the air" (p. 535).
Date: June 9, 1933
Creator: Truscott, Starr
Item Type: Refine your search to only Report
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Performance of a fuel-injection spark-ignition engine using a hydrogenated safety fuel

Description: This report presents the performance of a single-cylinder test engine using a hydrogenated safety fuel. The safety fuel has a flash point of 125 degrees f. (Cleveland open-dup method), which is high enough to remove most of the fire hazard, and an octane number of 95, which permits higher compression ratios to be used than are permissible with most undoped gasolines.
Date: June 13, 1933
Creator: Schey, Oscar W. & Young, Alfred W.
Item Type: Refine your search to only Report
open access

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.
Item Type: Refine your search to only Report
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A Possible Method for Preventing the Autorotation of Airplane Wings

Description: "At the suggestion of Professor Betz, the following device was tested with the object of reducing the autorotational speed of airplane wings. The model of a normal wing with the Gottigen profile 420, 1 meter span and 0.2 meter chord was provided with a pair of symmetrical slots on the suction side, connected with each other inside the wing. The arrangement of the testing equipment and models are given and the effect of the slots can be seen in the experimental curves that are included" (p. 1).
Date: June 1930
Creator: Schrenk, Oskar
Item Type: Refine your search to only Report
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Potential flow about arbitrary biplane wing sections

Description: From Summary: "A rigorous treatment is given of the problem of determining the two-dimensional potential flow around arbitrary biplane cellules. The analysis involves the use of elliptic functions and is sufficiently general to include the effects of such elements as the section shapes, the chord ratio, gap, stagger, and decalage, which elements may be specified arbitrarily. The flow problem is resolved by making use of the methods of conformal representation. Thus the solution of the problem o… more
Date: June 8, 1935
Creator: Garrick, I. E.
Item Type: Refine your search to only Report
open access

Preliminary Report on Laminar-Flow Airfoils and New Methods Adopted for Airfoil and Boundary-Layer Investigations

Description: "Recent developments in airfoil-testing methods and fundamental air-flow investigations, as applied to airfoils, are discussed. Preliminary test results, obtained under conditions relatively free from stream turbulence and other disturbances, are presented. Suitable airfoils and airfoil-design principles were developed to take advantage of the unusually extensive laminar boundary layers that may be maintained under the improved testing conditions" (p. 1).
Date: June 1939
Creator: Jacobs, Eastman N.
Item Type: Refine your search to only Report
open access

A preliminary study of flame propagation in a spark-ignition engine

Description: "The N.A.C.A. combustion apparatus was altered to operate as a fuel-injection, spark-ignition engine, and a preliminary study was made of the combustion of gasoline-air mixtures at various air-fuel ratios. Air-fuel ratios ranging from 10 to 21.6 were investigated. Records from an optical indicator and films from a high-speed motion-picture camera were the chief sources of data. Schlieren photography was used for an additional study" (p. 1).
Date: June 1937
Creator: Rothrock, A. M. & Spencer, R. C.
Item Type: Refine your search to only Report
open access

A preliminary study of the prevention of ice on aircraft by the use of engine-exhaust heat

Description: "An investigation was made in the N.A.C.A. ice tunnel at air temperatures from 20 degrees to 28 degrees Fahrenheit and at a velocity of 80 miles per hour to determine whether ice formations on a model wing could be prevented by the use of the heat from the engine-exhaust gas. Various spanwise duct systems were tested in a 6-foot-chord N.A.C.A. 23012 wing model. The formation of ice over the entire wing chord was prevented by the direct heating of the forward 10 percent of the wing by hot air, w… more
Date: June 1939
Creator: Rodert, Lewis A.
Item Type: Refine your search to only Report
open access

Preliminary Tests of Blowers of Three Designs Operating in Conjunction with a Wing-Duct Cooling System for Radial Engines, Special Report

Description: "This paper is one of several dealing with methods intended to reduce the drag of present-day radial engine installations and improve the cooling at zero and low air speeds. The present paper describes model wind-tunnel tests of blowers of three designs tested in conjunction with a wing-nacelle combination. The principle of operation involved consists of drawing cooling air into ducts located in the wing root at the point of maximum slipstream velocity, passing the air through the engine baffle… more
Date: June 1939
Creator: Biermann, David & Valentine, E. Floyd
Item Type: Refine your search to only Report
open access

Pressure-distribution measurements on the hull and fins of scale model of the U. S. Airship "Akron"

Description: This report presents the results of measurements of pressure distribution conducted in the propeller-research wind tunnel of the National Advisory Committee for Aeronautics on a 1/40-scale model of the U. S. Airship "Akron" (ZRS-4). The pressures, which were measured simultaneously at nearly 400 orifices located at 26 stations along one side of the hull, were recorded by two photographic multiple manometers placed inside the model. The hull pressures were measured both with and without the tail… more
Date: June 28, 1932
Creator: Freeman, Hugh B.
Item Type: Refine your search to only Report
open access

Pressure Rise, Gas Vibrations and Combustion Noises During the Explosion of Fuels

Description: "In the use of piezo-quartz indicators for high-speed automobile engines, the interpretation of pressure-time diagrams made by an oscillograph offers certain difficulties. On the one hand, the scale of the pressure amplitudes is not always the same under all conditions, while, on the other hand, the atmospheric zero line may be shifted from its correct position in the oscillogram. These facts make necessary to verify the readings of the quartz indicators by direct calibration before and after e… more
Date: June 1933
Creator: Wawrziniok
Item Type: Refine your search to only Report
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Principles involved in the cooling of a finned and baffled cylinder

Description: An analysis of the cooling problems for a finned cylinder is made on the basis of the known fundamental principles of heat transfer from pipes. Experimental results that support the analysis are presented. The results of previous investigations on the problem are evaluated on the basis of the analysis and the results. An illustration of the application of these principles to a specific problem is included.
Date: June 1938
Creator: Brevoort, M. J.
Item Type: Refine your search to only Report
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Propulsion by Reaction

Description: This report concerns propulsion by means of rockets. The author concerns himself mainly with efficiency of propulsion and he defines and mathematically expresses those efficiencies.
Date: June 1930
Creator: Roy, Maurice
Item Type: Refine your search to only Report
open access

Scale Effect on Clark Y Airfoil Characteristics From NACA Full-Scale Wind-Tunnel Tests

Description: This report presents the results of wind tunnel tests conducted to determine the aerodynamic characteristics of the Clark Y airfoil over a large range of Reynolds numbers. Three airfoils of aspect ratio 6 and with 4, 6, and 8 foot chords were tested at velocities between 25 and 118 miles per hour, and the characteristics were obtained for Reynolds numbers (based on the airfoil chord) in the range between 1,000,000 and 9,000,000 at the low angles of attack, and between 1,000,000 and 6,000,000 at… more
Date: June 14, 1934
Creator: Silverstein, Abe
Item Type: Refine your search to only Report
open access

A Simple Method for Increasing the Lift of Airplane Wings by Means of Flaps

Description: "Aerodynamic considerations led us, not long ago, to investigate a device which seemed to promise a contribution to the problem of reducing the landing speed of an airplane. We have subsequently learned that similar devices had already been proposed and investigated by others, but it seems advisable, nevertheless, to report our results. The problem is to create, in landing, a region of turbulence on the lower side of the wing near the trailing edge by some obstacle to the air flow" (p. 1).
Date: June 1933
Creator: Gruschwitz, Eugen & Schrenk, Oskar
Item Type: Refine your search to only Report
open access

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
Item Type: Refine your search to only Report
open access

Strength Tests of Thin-Walled Duralumin Cylinders in Compression

Description: "This report is the second of a series presenting the results of strength tests of thin-walled duralumin cylinders and truncated cones of circular and elliptic section. It contains the results obtained from compression tests on 45 thin-walled duralumin cylinders of circular section with ends clamped to rigid bulkheads. In addition to the tests on duralumin cylinders, there are included the results of numerous tests on rubber, celluloid, steel, and brass cylinders obtained from various sources" … more
Date: June 10, 1933
Creator: Lundquist, Eugene E.
Item Type: Refine your search to only Report
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A Suggested Method for Measuring Turbulence

Description: The desirability of a quantitative measure of turbulence is emphasized, and a possible method of attack on the problem is discussed. Data are presented to show that the hot-wire anemometer has possibilities as an instrument for measuring turbulence. An apparatus consisting essentially of two hot wire, one parallel to the air flow and one at right angles to it, is suggested.
Date: June 1931
Creator: Taylor, C. Fayette
Item Type: Refine your search to only Report
open access

Tables of Stiffness and Carry-Over Factor for Structural Members Under Axial Load

Description: "Tables of stiffness and carry-over factor are presented for members in which the cross section and axial load do not vary along the length of the member. These tables are of use in solving problems in the stability of structural members under axial load as well as in application of the Cross method of moment distribution when the effects of axial load in the members are considered. The interval between successive values of the argument is small enough to make interpolation unnecessary in engin… more
Date: June 1938
Creator: Lundquist, Eugene E. & Kroll, W. D.
Item Type: Refine your search to only Report
open access

Tank tests of model 11-G flying-boat hull

Description: "The NACA model 11-G flying-boat hull, a modification of NACA model 11-A was tested over a range of loadings. The planing bottom of model 11-G has a variable-radius flare, or concavity, at the chines in contrast to the straight V planing bottom of model 11-A. The results are given as curves of resistance and trimming moment plotted against speed for various angles of trim" (p. 1).
Date: June 1935
Creator: Parkinson, J. B.
Item Type: Refine your search to only Report
open access

Tank tests of NACA model 40 series of hulls for small flying boats and amphibians

Description: From Summary: "The NACA model 40 series of flying-boat hull models consists of 2 forebodies and 3 afterbodies combined to provide several forms suitable for use in small marine aircraft. One forebody is the usual form with hollow bow sections and the other has a bottom surface that is completely developable from bow to step. The afterbodies include a short pointed afterbody with an extension for the tail surfaces, a long afterbody similar to that of a seaplane float but long enough to carry the… more
Date: June 19, 1935
Creator: Parkinson, John B. & Dawson, John R.
Item Type: Refine your search to only Report
open access

Tank Tests of the Effect of Rivet Heads, etc., on the Water Performance of a Seaplane Float, Special Report

Description: "A 1/3.5 full-size model of the Mark V float of the Bureau of Aeronautics, Navy Department, was tested in the NACA tank both with smooth painted bottom surfaces and with roundhead rivets, plate laps, and keel plates fitted to simulate the actual bottom of a metal float. The augmentation in water resistance due to the added roughness was found to be from 10-12% at the hum speed and from 12-14% at high speeds. The effect of the roughness of the afterbody was found to be negligible except at high … more
Date: June 4, 1936
Creator: Parkinson, J. B. & Robertson, J. B., Jr.
Item Type: Refine your search to only Report
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