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Aerodynamic Characteristics of Three Deep-Stepped Planing-Tail Flying-Boat Hulls

Description: "An investigation was made in the Langley 300 MPH 7- by 10-foot tunnel to determine the aerodynamic characteristics of three deep-stepped planing-tail flying-boat hulls differing only in the amount of step fairing. The hulls were derived by increasing the unfaired step depth of a planing-tail hull of a previous aerodynamic investigation to a depth about 92 percent of the hull beam. Tests were also made on a transverse-stepped hull with an extended afterbody for the purpose of comparison and in … more
Date: March 13, 1947
Creator: Riebe, John M. & Naeseth, Rodger L.
Item Type: Refine your search to only Report
open access

Altitude-Wind-Tunnel Investigation of R-4360-18 Power-Plant Installation for XR60 Airplane, 3, Performance of Induction and Exhaust Systems

Description: From Summary: "A study has been made of the performance of the induction and the exhaust systems on the XR60 power-plant installation as part of an investigation conducted in the Cleveland altitude wind tunnel. Altitude flight conditions from 5000 to 30,000 feet were simulated for a range of engine powers from 750 to 3000 brake horsepower."
Date: March 28, 1947
Creator: Dupree, David T. & Hawkins, W. Kent
Item Type: Refine your search to only Report
open access

Buckling Stresses of Simply Supported Rectangular Flat Plates in Shear

Description: "The present paper evaluates the shear buckling stresses of rectangular flat plates with simply supported edges more accurately than previous work on this problem. Both symmetric (odd number of buckles) and antisymmetric (even number of buckles) patterns were considered. A curve is presented from which the critical stresses may be obtained when the dimensions of the plate are known" (p. 1).
Date: March 1947
Creator: Stein, Manuel & Neff, John
Item Type: Refine your search to only Report
open access

A collection of the collapsed results of general tank tests of miscellaneous flying-boat-hull models

Description: Presented here are the summary charts of the collapsed results of general tank tests of about 100 flying boat hull models. These summary charts are intended to be used as an engineering tool to enable a flying boat designer to grasp more quickly the significance of various hull form parameters as they influence his particular airplane. The form in which the charts are prepared is discussed in some detail in order to make them clearer to the designer. This is a data report, and no attempt has be… more
Date: March 1947
Creator: Locke, F. W. S., Jr.
Item Type: Refine your search to only Report
open access

Comparative Drag Measurements at Transonic Speeds of an NACA 65-006 Airfoil and a Symmetrical Circular-Arc Airfoil

Description: Report presenting measurements made at transonic speeds by the freely-falling-body method to compare the drag of a rectangular plan-form airfoil of aspect ratio 7.6 with an NACA 65-006 airfoil section. Results regarding the velocity measurements, base-pressure measurements, and airfoil drag measurements are provided.
Date: March 6, 1947
Creator: Thompson, Jim Rogers & Marschner, Bernard W.
Item Type: Refine your search to only Report
open access

Comparative Tests on Extruded 14S-T and Extruded 24S-T Hat-Shape Stiffener Sections

Description: Note presenting an investigation to compare the 14S-T with 24S-T in extruded stiffeners for stiffened flat sheet panels. The tests were made with stiffened flat sheet panels with three hat-shape stiffeners. Data is provided on the strength of the two alloys as well as the effect of sheet thickness on relative stiffener strengths.
Date: March 1947
Creator: Holt, Marshall & Feil, G. W.
Item Type: Refine your search to only Report
open access

Cooling of Gas Turbines, 2, Effectiveness of Rim Cooling of Blades

Description: An analysis is presented of rim cooling of gas-turbine blades; that is, reducing the temperature at the base of the blade (wheel rim), which cools the blade by conduction alone. Formulas for temperature and stress distributions along the blade are derived and, by the use of experimental stress-rupture data for a typical blade alloy, a relation is established between blade life (time for rupture), operating speed, and amount of rim cooling for several gas temperatures. The effect of blade parame… more
Date: March 18, 1947
Creator: Wolfenstein, Lincoln; Meyer, Gene L. & McCarthy, John S.
Item Type: Refine your search to only Report
open access

Critical Combinations of Shear and Direct Stress for Simply Supported Rectangular Flat Plates

Description: Note presenting an investigation of the buckling of a simply supported rectangular flat plate under combinations of shear and direct stress by means of an energy method. The critical combinations of stress for several length-width ratios were determined to an accuracy of about 1 percent in conjunction with a modified matrix iteration method. Results regarding the shear and longitudinal stress and shear and transverse stress are provided.
Date: March 1947
Creator: Batdorf, S. B. & Stein, Manuel
Item Type: Refine your search to only Report
open access

Critical Stress of Thin-Walled Cylinders in Axial Compression

Description: Empirical design curves are presented for the critical stress of thin-wall cylinders loaded in axial compression. These curves are plotted in terms of the nondimensional parameters of small-deflection theory and are compared with theoretical curves derived for the buckling of cylinders with simply supported and clamped edges. An empirical equation is given for the buckling of cylinders having a length-radius ratio greater than about 0.75.
Date: March 20, 1947
Creator: Batdorf, S. B.; Schildcrout, Murry & Stein, Manuel
Item Type: Refine your search to only Report
open access

Data on Optimum Length, Shear Strength, and Tensile Strength of Age-Hardened 17S-T Machine-Countersunk Rivets in 75S-T Sheet

Description: Report presenting a series of tensile-strength and shear-strength tests made on age-hardened 17S-T rivets machine-countersunk in 75S-T sheets. The results of the tests indicated that the joints can be made satisfactorily with regard to both flushness and strength if the ratio of buck to diameter is kept to a certain value.
Date: March 1947
Creator: Schuette, Evan H. & Niles, Donald E.
Item Type: Refine your search to only Report
open access

Determination of Ram-Jet Combustion-Chamber Temperatures by Means of Total-Pressure Surveys

Description: "A method is described by which the total temperature of the gases at the combustion-chamber outlet of a ram-jet engine may be determined from the loss in total pressure measured across the combustion chamber. A working chart is presented by means of which the ratio of the total temperature of the gases at the combustion-chamber outlet to the total temperature of the gases at the combustion-chamber inlet may be determined from the measured loss of total pressure across the combustion chamber an… more
Date: March 3, 1947
Creator: Pinkel, I. Irving
Item Type: Refine your search to only Report
open access

Distribution of Boron in Processing of Carnotite Concentrate

Description: It was desired to determine the distribution of boron in the various steps of the processing of domestic ore concentrates containing high percentages of boron. The experiments described in this report were directed toward that end. Summary of this report are: (1) a black oxide containing 0.6 ppm of boron was prepared from material containing 350 ppm; (2) less than 0.02% of the boron in the original material appeared in the black oxide; (3) the iron step did not remove appreciable amounts of bor… more
Date: March 13, 1947
Creator: O'Connors, R. J.
Item Type: Refine your search to only Report
open access

Ditching Tests of a 1/18-Scale Model of the Navy XP4M-1 Airplane in Langley Tank No. 2 and on an Outdoor Catapult, TED No. NACA 2362

Description: From Summary: "Tests with a dynamically similar model of the Navy XP4M-1 airplane were made to determine the best way to land the airplane in calm and rough water, to determine its probable ditching performance, and to determine practicable modifications which could be incorporated in the design of the airplane that would improve its ditching characteristics. The results were obtained by making visual observations, by recording longitudinal decelerations ,and by taking motion pictures of the la… more
Date: March 10, 1947
Creator: Fisher, Lloyd J. & Hoffman, Edward L.
Item Type: Refine your search to only Report
open access

Ditching Tests with a 1/12-Scale Model of the Army A-26 Airplane in Langley Tank No. 2 and on an Outdoor Catapult

Description: Tests were conducted in calm water in Langley tank no. 2 and in calm and rough water at an outdoor catapult in order to determine the best way to make a forced landing of an Army A-26 airplane and to determine its probable ditching behavior. These tests were requested by the Air Materiel Command, Army Air Forces, in their letter of March 26, 1943, WEL:AW:50.
Date: March 6, 1947
Creator: Jarvis, George A. & Hoffman, Edward L.
Item Type: Refine your search to only Report
open access

Ditching Tests with a 1/16-Size Model of the Navy XP2V-1 Airplane at the Langley Tank No. 2 Monorail

Description: "Tests were made with a 1/16 size dynamically similar model of the Navy XP2V-1 airplane to study its performance when ditched. The model was ditched in calm water at the Langley tank no. 2 monorail. Various landing attitudes, speeds, and conditions of damage were simulated" (p. 1).
Date: March 14, 1947
Creator: Fisher, Lloyd J. & Tarshis, Robert P.
Item Type: Refine your search to only Report
open access

Drag Measurements of Symmetrical Circular-Arc and NACA 65-009 Rectangular Airfoils Having an Aspect Ratio of 2.7 as Determined by Flight Tests at Supersonic Speeds

Description: Report discussing testing to determine the drag characteristics at zero lift of a wing with a circular-arc airfoil section with a maximum thickness of 9 percent chord. The results were compared to previous testing on an NACA 65-009 airfoil. It was found that the NACA airfoil had lower drag coefficients than the circular-arc airfoil tested in this experiment.
Date: March 7, 1947
Creator: Alexander, Sidney R.
Item Type: Refine your search to only Report
open access

Drag of a Wing-Body Configuration Consisting of a Swept-Forward Tapered Wing Mounted on a Body of Fineness Ratio 12 Measured During Free Fall at Transonic Speeds

Description: Report discussing an investigation to determine the drag of a configuration with a body of fitness ratio 12 with stabilizing tail surfaces and a 12-percent-thick 30-degree swept-forward wing using the free-fall method. The drag oft he wing and the total drag were measured separately and compared. The swept-forward wing was found to greatly increase the effect of drag on the body-tail combination.
Date: March 13, 1947
Creator: Thompson, Jim Rogers & Mathews, Charles W.
Item Type: Refine your search to only Report
open access

Effect of combustor-inlet conditions on performance of an annular turbojet combustor

Description: From Summary: "The combustion performance, and particularly the phenomenon of altitude operational limits, was studied by operating the annular combustor of a turbojet engine over a range of conditions of air flow, inlet pressure, inlet temperature, and fuel flow. Information was obtained on the combustion efficiencies, the effect on combustion of inlet variables, the altitude operational limits with two different fuels, the pressure losses in the combustor, the temperature and velocity profile… more
Date: March 21, 1947
Creator: Childs, J. Howard; McCafferty, Richard J. & Surine, Oakley W.
Item Type: Refine your search to only Report
open access

Effect of Compressibility at High Subsonic Velocities on the Moment Acting on an Elliptic Cylinder

Description: Note presenting the utilization of an extended form of the Ackeret iteration process to calculate the compressible flow at high subsonic velocities past an elliptical cylinder. The expression for the moment acting on the elliptical cylinder is derived and shows a first-step improvement of the Prandtl-Glauert approximation. A second-step improvement is obtained in the Prandtl-Glauert approximation for the lifting force acting on the elliptic cylinder.
Date: March 1947
Creator: Kaplan, Carl
Item Type: Refine your search to only Report
open access

Effect of Exhaust Pressure on the Cooling Characteristics of an Air-Cooled Engine

Description: Report presenting the results of a cooling investigation using an 18-cylinder, radial, air-cooled engine installed on a dynamometer test stand to determine the effects of exhaust pressure on the engine-cooling characteristics. Testing covered a wide variety of engine operating conditions.
Date: March 1947
Creator: Valerino, Michael F.; Kaufman, Samuel J. & Hughes, Richard F.
Item Type: Refine your search to only Report
open access

Effect of Exhaust Pressure on the Performance of an 18-Cylinder Air-Cooled Radial Engine with a Valve Overlap of 40 Degrees

Description: Note presenting an investigation to determine the effect of exhaust pressure on the performance of an 18-cylinder air-cooled radial engine equipped with a conventional exhaust collector ring. The engine power increased at a diminishing rate as exhaust pressure decreased.
Date: March 1947
Creator: Boman, David S.; Nagey, Tibor F. & Doyle, Ronald B.
Item Type: Refine your search to only Report
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