Technical Report Archive & Image Library (TRAIL) - 30,113 Matching Results

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An investigation of a four-blade single-rotation propeller in combination with an NACA 1-series D-type cowing at Mach numbers up to 0.83

Description: Report presenting an investigation of a four-blade single-rotation propeller in combination with an NACA 1-series D-type spinner-cowling combination at Mach numbers up to 0.83. Characteristics of the propeller operating in the presence of the cowling are compared with the characteristics of the propeller with the spinner.
Date: April 13, 1953
Creator: Reynolds, Robert M.; Sammonds, Robert I. & Kenyon, George C.
Partner: UNT Libraries Government Documents Department
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Tests in the Ames 40- by 80-foot wind tunnel of an airplane configuration with an aspect ratio 3 triangular wing and an all-movable horizontal tail: Longitudinal and lateral characteristics

Description: Report presenting an investigation to determine the low-speed large-scale characteristics of an aspect ratio 3 triangular-wing airplane model. The model consisted of the wing in combination with a fuselage of fitness ratio 12.5, a thin, triangular vertical tail with a constant-chord rudder, and a thin, unswept, all-movable tail.
Date: April 13, 1953
Creator: Koenig, David G.
Partner: UNT Libraries Government Documents Department
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Thermal Annealing of Neutron Induced Discomposition in Artificial Graphite : [Part] III, Heating-During-Irradiation Experiments

Description: Experiments are described in which the pile-induced changes in electrical resistivity and elastic modulus of graphite were investigated as functions of the sample temperature during bombardment and the amount of bombardment. The data are for relatively low bombardment times (up to ca. 20 L-units) and temperatures (up to 340*C) and are not sufficiently extensive to permit unequivocal conclusions.
Date: April 13, 1953
Creator: Neubert, T. J.
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation of the Static Lateral Stability Characteristics of Wing-Fuselage Combinations at High Subsonic Speeds

Description: A systematic research program is being carried out in the Langley high-speed 7- by 10-foot tunnel to determine the aerodynamic characteristics of various arrangements of the component parts of research-type airplane models, including some complete model configurations. Data are being obtained on characteristics in pitch, sideslip, and during steady roll at Mach numbers from 0.40 to about 0.95. This paper presents results which show the effect of taper ratio on the aerodynamic characteristics in… more
Date: April 10, 1953
Creator: Wiggins, James W. & Fournier, Paul G.
Partner: UNT Libraries Government Documents Department
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Analysis of Heat Transfer and Fluid Friction for Fully Developed Turbulent Flow of Supercritical Water With Variable Fluid Properties in a Smooth Tube

Description: From Summary: "Calculated velocity and temperature distributions, as well as relations among Nusselt number, Reynolds number, and friction factor, are presented. The effect of variation of fluid properties across the tube on the Nusselt number and friction factor correlations can be eliminated by evaluating the properties at a reference temperature which is a function of both the wall temperature and the ratio of wall-to-bulk temperatures."
Date: April 9, 1953
Creator: Deissler, Robert G. & Taylor, Maynard F.
Partner: UNT Libraries Government Documents Department
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Analytical Studies of the Response to Longitudinal Control of Three Airplane Configurations in Landing Approaches

Description: Memorandum presenting a theoretical investigation to determine the reasons for poor airplane response to longitudinal control. Some effects of airplane configuration on the response, primarily for short time periods, were also determined. Results regarding a comparison of three airplanes, the effect of changes on airplane B, and the effect of changes on airplane C are provided.
Date: April 9, 1953
Creator: Bihrle, William, Jr. & Stone, Ralph W., Jr.
Partner: UNT Libraries Government Documents Department
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Analytical studies of the response to longitudinal control of three airplane configurations in landing approaches

Description: From Introduction: "A theoretical investigation was conducted in order to determine what effect the differences in aerodynamic characteristics would have on the short-time response to elevator control of this type of airplane as compared with the responses of a conventional airplane, without regard to any possible psychological influences. The results of this investigation are presented in this paper."
Date: April 9, 1953
Creator: Bihrle, William, Jr. & Stone, Ralph W., Jr.
Partner: UNT Libraries Government Documents Department
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Design procedure and limited test results for a high solidity, 12-inch transonic impeller with axial discharge

Description: Report presenting an approximate inverse impeller design procedure based on the assumption of axisymmetric, nonviscous flow along with some limited experimental data obtained from a high solidity, 12-inch transonic impeller. The design procedure includes a point-by-point solution of the impeller flow conditions along a series of streamlines in the radial-axial plane. Results regarding the overall performance, impeller flow limits, and blade structural failure are provided.
Date: April 9, 1953
Creator: Wright, Linwood C. & Kovach, Karl
Partner: UNT Libraries Government Documents Department
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Performance of a 13-Stage Development Compressor for the J40-WE-24 Engine at Equivalent Speeds from 30 to 112 Percent of Design

Description: The performance of a 13-stage development compressor for the J40-WE-24 engine has been determined at equivalent speeds from 30 to 112 percent of design. The design total-pressure ratio of 6.0 and the design weight flow of 164 pounds per second were not attained, An analysis was conducted to determine the reasons for the poor performance at the design and over-design speed. The analysis indicated that most of the difficulty could be attributed to the fact that the first stage was overcompromised… more
Date: April 9, 1953
Creator: Hatch, James E.; Lucas, James G. & Finger, Harold B.
Partner: UNT Libraries Government Documents Department
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Use of flame-immersed blades to improve combustion limits and efficiency of a 5-inch diameter connected-pipe, ram-jet combustor

Description: Report presenting the effects of flame-immersed blades on combustion stability and efficiency, which were determined at various combustor-inlet conditions by use of several geometric blade arrangements, two fuels, two fuel-injection systems, and two blade temperatures. Specific combustor configurations with flame-immersed blades showed marked improvement in stability and efficiency. The operational life of the blades was also observed to be excellent.
Date: April 9, 1953
Creator: Male, Donald W.
Partner: UNT Libraries Government Documents Department
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A Ball Holder for Coating Operations

Description: A device has been designed which will support small spheres and cylinders in a vacuum system during a plating operation. While supporting the object to be plated, the device automatically shifts the position of the supports so that the coating is evenly distributed. This report describes the mechanism by which this motion is achieved.
Date: April 8, 1953
Creator: Lilienthal, James R.
Partner: UNT Libraries Government Documents Department
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Damping in Pitch of Low-Aspect-Ratio Wings at Subsonic and Supersonic Speeds

Description: Memorandum presenting the application of the concept of indicial functions to the analysis of the aerodynamic phenomena associated with the short-period pitching mode of wings in subsonic and supersonic flight. Simple physical relationships are pointed out and are used to study the effect on the rotary-damping-moment coefficient of changes in center-of-gravity position, Mach number, aspect ratio, plan form, frequency, and thickness.
Date: April 8, 1953
Creator: Tobak, Murray
Partner: UNT Libraries Government Documents Department
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Effects of Span and Spanwise and Chordwise Location on the Control Effectiveness of Spoilers on a 50 Degree Sweptback Wing at Mach Numbers of 1.41 and 1.96

Description: Memorandum presenting an investigation in the supersonic blowdown tunnel to determine the effects of span and spanwise and chordwise location on the control characteristics of spoilers on a 6-percent-thick, 50 degrees sweptback wing of aspect ratio 2.5 and taper ratio of 0.625. The results of the investigation indicate that the inboard spoilers located at the rearward chordwise station produce the highest rolling-moment effectiveness.
Date: April 8, 1953
Creator: Kindell, William H.
Partner: UNT Libraries Government Documents Department
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Effects of slot size and geometry on the flow in rectangular tunnels at Mach numbers up to 1.4

Description: Report presenting an investigation of the effects of slot width, depth, shape, and spacing on the center-line pressure distribution in rectangular tunnels of constant cross section with several height-to-width ratios. Results are presented in the form of center-line static-pressure distributions and calculated static-pressure and angle-of-flow distributions along the slotted boundary.
Date: April 7, 1953
Creator: Nelson, William J. & Cubbage, James M., Jr.
Partner: UNT Libraries Government Documents Department
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The Heat of Formation of Thorium Sesquisulfide

Description: Abstract: "The heat of solution of thorium sesquisulfide was determined in 6.000 molar HCl at 25 C to ascertain the stability of the thorium (III) halides. The molal heat of formation of Th2S3 from rhombic sulfur and crystalline thorium is calculated as 258.6 kcal."
Date: April 7, 1953
Creator: Eyring, LeRoy & Westrum, Edgar F., Jr.
Partner: UNT Libraries Government Documents Department
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Langley full-scale-tunnel tests of the Custer Channel Wing airplane

Description: Memorandum presenting testing of an experimental Custer Channel Wing airplane in the full-scale tunnel to investigate the lift characteristics of a channel-propeller combination and the flow phenomena in and about a channel wing.
Date: April 7, 1953
Creator: Pasamanick, Jerome
Partner: UNT Libraries Government Documents Department
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A method for calculating the aerodynamic loading on wing-tip-tank combinations in subsonic flow

Description: From Summary: "An analytical method for calculating the aerodynamic loading on wing-tip-tank combinations in subsonic flow is developed by using a simple horseshoe vortex-image system for the case of the tank axis in the plane of the wing. An illustrative example is given in the appendix, in which wing and tip-tank loadings are calculated for three configurations. The calculated results are shown to be in good agreement with experimental data."
Date: April 7, 1953
Creator: Robinson, Samuel W., Jr. & Zlotnick, Martin
Partner: UNT Libraries Government Documents Department
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Multigroup Analysis on the IBM 604

Description: This is a preliminary report on a multigroup's analysis on the IBM 604, a programmable Electronic Calculating Punch, as part of the course work W31-Eng. 52.
Date: April 7, 1953
Creator: Stark, R. H.; Hibbert, C. & Ryan, D. Z.
Partner: UNT Libraries Government Documents Department
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A Theoretical Analysis of the Distortion of Fuel-Spray-Particle Paths in a Helicopter Ram-Jet Engine Due to Centrifugal Effects

Description: Report presenting a theoretical study of certain anomalies in the behavior of a ram-jet engine engine tip-mounted on a rotating helicopter blade that appears to be related to centrifugal effects distorting the fuel-spray pattern. Results regarding the cases calculated, results of the calculations, particle-path distortion, and limiting direction of particle paths are provided.
Date: April 7, 1953
Creator: Katzoff, S. & Smith, Samuel L., III
Partner: UNT Libraries Government Documents Department
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Theoretical study of the tunnel-boundary lift interference due to slotted walls in the presence of the trailing-vortex system of a lifting model

Description: Report presenting some equations that give the interference on the trailing-vortex system of a uniformly loaded finite-span wing in a circular tunnel containing partly open and partly closed walls, with special reference to symmetrical arrangements of the open and closed portions. Methods are given for extending the equations to include tunnel shapes other than circular.
Date: April 7, 1953
Creator: Matthews, Clarence W.
Partner: UNT Libraries Government Documents Department
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Aerodynamics of slender bodies at Mach number of 3.12 and Reynolds numbers from 2 x 10(exp 6) to 15 x 10(exp 6) 3: boundary layer and force measurements on a slender cone-cylinder body of revolution

Description: Report presenting an experimental investigation to determine the aerodynamic characteristics of a slender cone-cylinder body of revolution in the 1- by 1-foot supersonic wind tunnel. Viscous drag and three component forces were measured at Mach number 3.12 and a range of Reynolds numbers and angles of attack. Results regarding pressure distributions, boundary layer, and forces are provided.
Date: April 6, 1953
Creator: Jack, John R.
Partner: UNT Libraries Government Documents Department
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Altitude Starting Characteristics of an Afterburner With Autoignition and Hot-Streak Ignition

Description: "Ignition of the fuel-air mixture in an afterburner of turbojet engine at altitude has often proved to be a different problem to solve. Electrical ignition has not proven satisfactory because of the unreliability of such systems (ref. 1). The ignition data reported herein were obtained for two after-burner configurations. Autoignition data are included for both configurations and hot-streak-ignition data, for only one. "
Date: April 6, 1953
Creator: Renas, P. E.; Harvey, R. W., Sr. & Jansen, E. T.
Partner: UNT Libraries Government Documents Department
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The Design of Brittle-Material Blade Roots Based on Theory and Rupture Tests of Plastic Models

Description: "Theoretical design charts based on Neuber's equations for symmetrically located notches are presented for estimating the approximate rupture strengths of blade roots made from brittle materials. The limit of applicability of the theoretical charts is shown as determined by rupture tests of plastic models. The optimum proportions among over-all root width, neck width, notch radius, and notch depth are determined from the design charts" (p. 1).
Date: April 6, 1953
Creator: Meyer, André J., Jr.; Kaufman, Albert & Caywood, William C.
Partner: UNT Libraries Government Documents Department
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