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Combustion-engine temperatures by the sodium line-reversal method

Description: The sodium line-reversal method has been used in some preliminary measurements of flame temperature. Improvements in the method involving a photographic recorder and a means of correcting for the dirtiness of the windows are described. The temperatures so obtained are compared with those calculated from pressure diagrams.
Date: March 1936
Creator: Brevoort, Maurice J.
Partner: UNT Libraries Government Documents Department
open access

Air flow in the boundary layer near a plate

Description: From Summary: "The published data on the distribution of speed near a thin flat plate with sharp leading edge placed parallel to the flow (skin friction plate) are reviewed and the results of some additional measurements are described. The purpose of the experiments was to study the basic phenomena of boundary-layer flow under simple conditions."
Date: March 1936
Creator: Dryden, Hugh L.
Partner: UNT Libraries Government Documents Department
open access

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
open access

Ignition and Flame Development in the Case of Diesel Fuel Injection

Description: "To investigate the process of ignition and combustion in the case of spray injection into heated air, a new form of apparatus is developed and the tests carried out with it described. Photographs of the spray before and after ignition are obtained at frequencies of 500 pictures per second. Pressures and temperatures are simultaneously recorded on oscillograms. Information on the initial conditions, ignition time lag, period of complete combustion, place where ignition starts, and general cours… more
Date: March 1936
Creator: Holfelder, Otto
Partner: UNT Libraries Government Documents Department
open access

The 5- by 7-meter wind tunnel of the DVL

Description: The report contains a description of the DVL wind tunnel. According to the cones fixed, an elliptical stream with axes 5 by 7 meters and length 9 meters, or a stream 6 by 8 meters in cross section and 11 meters in length is available. The top speed with the smaller cone is 65 meters per second. The testing equipment consists of an automatic six-component balance and a test rig for propellers and engines up to 650 horsepower.
Date: March 1936
Creator: Kramer, M.
Partner: UNT Libraries Government Documents Department
open access

Full-scale wind-tunnel to determine a satisfactory location for a service Pitot-static tube on a low-wing monoplane

Description: Surveys of the air flow over the upper surface of four different airfoils were made in the full-scale wind tunnel to determine a satisfactory location for a fixed Pitot-static tube on a low-wing monoplane. The selection was based on small interference errors, less than 5 percent, and on a consideration of structural and ground handling problems. The most satisfactory location on the airfoils without flaps that were investigated was 10 percent of the chord aft and 25 percent of the chord above t… more
Date: March 1936
Creator: Parsons, John F.
Partner: UNT Libraries Government Documents Department
open access

Calculated and measured pressure distributions over the midspan section of the NACA 4412 airfoil

Description: Pressures were simultaneously measured in the variable-density tunnel at 54 orifices distributed over the midspan section of 5 by 30 inch rectangular model of the NACA 4412 airfoil at 17 angles of attack ranging from -20 degrees to 30 degrees at a Reynolds number of approximately 3,000,000. Accurate data were thus obtained for studying the deviations of the results of potential-flow theory from measured results. The results of the analysis and a discussion of the experimental technique are pres… more
Date: March 25, 1936
Creator: Pinkerton, Robert M.
Partner: UNT Libraries Government Documents Department
open access

Effect of nozzle design on fuel spray and flame formation in a high-speed compression-ignition engine

Description: "Fuel was injected from different type of injection nozzles into the combustion chamber of the NACA combustion apparatus, operated as a compression-ignition engine. High speed motion pictures were taken of the fuel sprays and combustion. Single-orifice nozzles of 0.008, 0.020, and 0.040 inch diameter, and multiorifice nozzles having 2, 6, and 16 orifices were tested. Nozzles having impinging jets and slit orifices were also included" (p. 327).
Date: March 19, 1936
Creator: Rothrock, A. M. & Waldron, C. D.
Partner: UNT Libraries Government Documents Department
open access

The Performance of a DePalma Roots-Type Supercharger

Description: "The results of tests made to determine the performance of a DePalma-Roots supercharger are presented. The performance of the DePalma supercharger with atmospheric pressure at the discharge was compared with that of a hypothetical NACA Roots-type supercharger of the same displacement. The tests were conducted at speeds from 1,000 to 6,000 r.p.m. and at pressure differences from 0 to 15 inches of mercury" (p. 1).
Date: March 1936
Creator: Schey, Oscar W. & Ellerbrock, Herman H., Jr.
Partner: UNT Libraries Government Documents Department
open access

Interference of Wing and Fuselage From Tests of 28 Combinations in the N.A.C.A. Variable-Density Tunnel

Description: Report presents the results of tests conducted on 28 wing-fuselage combinations made in the variable-density wind tunnel as a part of the wing-fuselage interference program being conducted therein and in addition to the 209 combinations previously reported in NACA-TR-540. These tests practically complete the study of combinations with a rectangular fuselage and continue the study of combinations with a round fuselage and a tapered wing.
Date: March 12, 1936
Creator: Sherman, Albert
Partner: UNT Libraries Government Documents Department
open access

A Comparison of Corrosion-Resistant Steel (18 Percent Chromium - 8 Percent Nickel) and Aluminum Alloy (24st)

Description: "In the selection of materials for aircraft application, it is not enough to make the selection on a strength-weight basis alone. A strength-weight comparison is significant but other factors must be considered, for while a material with a high ratio of strength to weight may be perfectly satisfactory for one use, it may be totally unfitted for another. It is essential, among other things, that the probable nature, magnitude, and direction of the principal stresses be given special consideratio… more
Date: March 1936
Creator: Sullivan, J. E.
Partner: UNT Libraries Government Documents Department
open access

The Latécoère 521 "Lieutenant De Vaisseau Paris" Commercial Flying Boat (French): A Two-Deck Six-Engine Semicantilever Sesquiplane

Description: Circular presenting a description of the Latécoère 521, which was the largest aircraft built in France at the time. A more detailed description of the wings, hull, accommodation for passengers and officers, fuel system, controls, and flight characteristics is provided.
Date: March 1936
Partner: UNT Libraries Government Documents Department
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