Technical Report Archive & Image Library (TRAIL) - 145 Matching Results

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Aerodynamic Characteristics of a Refined Deep-Step Planing-Tail Flying-Boat Hull with Various Forebody and Afterbody Shapes

Description: From Introduction: "The results of one phase of this investigation, presented in reference 1, have indicated that hull drag can be reduced without causing large changes in aerodynamic stability and hydrodynamic performance by the use of high length-beam ratios. Another phase of the investigation, reference 2, indicated that hulls of the deep-step planning-tail type have much lower air drag than the conventional type of hull and about the same aerodynamic stability; tank tests, reference 3, have… more
Date: June 1952
Creator: Riebe, John M. & Naeseth, Rodger L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Aerodynamic Design of High Mach Number Nozzles Utilizing Axisymmetric Flow with Application to a Nozzle of Square Test Section

Description: From Introduction: "A method for the design of three-dimensional nozzles based on axi-symmetric flow is presented in this paper. The design method presented in this paper is general; however, as an illustrative example of the design of a Mach number 10 nozzle with square test section is included."
Date: June 1952
Creator: Beckwith, Ivan E.; Ridyard, Herbert W. & Cromer, Nancy
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Alloys of Uranium with Zirconium, Chromium, Columbium, Vanadium, and Molybdenum

Description: Abstract: Information on five uranium binary alloy systems has been surveyed. These systems are the alloys of uranium with zirconium, chromium, columbium, vanadium, and molybdenum. The equilibrium diagrams are discussed, and where available, data have been included on diffusion studies, cladding experiments, and mechanical properties.
Date: June 19, 1952
Creator: Saller, Henry A. & Rough, Frank A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Altitude performance investigation of single- and double-annular turbojet-engine combustors with various size fuel nozzles

Description: From Introduction: "The purpose of the investigation conducted at the NACA Lewis laboratory and reported herein was to determine the improvements possible in full-scale turbojet-engine performance when a single-annular combustor with slotted air-inlet orifices was used."
Date: June 9, 1952
Creator: Harp, James L., Jr. & Vincent, Kenneth R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Altitude Wind Tunnel Investigation of High-Temperature Afterburners

Description: From Introduction: "During previous investigations of afterburning conducted at the NACA Lewis laboratory (references 1 to 4, for example), the objective of obtaining high exhaust-gas temperatures and, consequently, maximum thrust augmentation was compromised to some extent in order to alleviate the problem of afterburner shell cooling. The primary objective of the investigation reported herein was therefore the attainment of maximum exhaust-gas temperature imposed by the cooling techniques pre… more
Date: June 26, 1952
Creator: Conrad, E. William & Campbell, Carl E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analogue-computer simulation of an autopilot servo system having nonlinear response characteristics

Description: From Introduction: "The servo system considered in this report is in the latter category, due mainly to the fact its amplifier tends to saturate. An investigation of the longitudinal dynamic response of the stabilized airplane was made and the results were reported in reference 1. In this investigation it was found that when restricted to linear methods of analysis the performance of the autopilot-aircraft combination could be predicted for only the small range of operation where the elements o… more
Date: June 1952
Creator: Jones, Arthur L. & White, John S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analysis of Stage Matching and Off-Design Performance of Multistage Axial-Flow Compressors

Description: From Introduction: "The present report is intended to give a qualitative picture of the operation of each stage of a multistage compressor over a range of actual operating conditions from 50 to 100 percent design speed and to point out some means of achieving improved off-design performance. The method used in the report is primarily analytical and is based on single-stage-performance results."
Date: June 27, 1952
Creator: Finger, Harold B. & Dugan, James F., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Analysis of Supersonic Flow in the Region of the Leading Edge of Curved Airfoils, Including Charts for Determining Surface-Pressure Gradient and Shock-Wave Curvature

Description: Note presenting an investigation of the inviscid flow in the region of the leading edge of curved airfoils with attached shock waves. Tables and charts are presented for determining the surface-pressure gradient and the shock-wave curvature in supersonic flow of an ideal diatomic gas. An approximate procedure for determining the flow field a short distance downstream of the leading edge is also presented.
Date: June 1952
Creator: Kraus, Samuel
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Analysis of the Effect of Structural Feedback on the Flutter of a Control Surface Having a Power-Boost System

Description: From Summary: "Such devices as leading- and trailing-edge flaps which are now in use on operational aircraft permit the attainment of maximum airplane lift coefficients, power-off, of the order of 2.8 (reference 1). Airfoil-section maximum lift coefficients as high as 5.5 have been obtained in wind-tunnel tests (see, for example, reference 2), and in a limited flight investigation airplane lift coefficients of 4.2 were obtained (reference 3)."
Date: June 10, 1952
Creator: Barnes, Robert H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Analytical Study of the Comparative Performance of Four Air-Induction Systems for Turbojet-Powered Airplanes Designed to Operate at Mach Numbers Up to 1.5

Description: Memorandum presenting a study made to ascertain some of the operational characteristics of four types of air-induction systems for a turbojet-powered airplane intended to operate at a range of Mach numbers at an altitude of 35,332 feet. The investigation included air-induction systems with and wthout ramps to produce oblique shock waves, with fixed and variable inlet areas, and with divergent diffusers.
Date: June 17, 1952
Creator: Blackaby, James R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An approximate method of determining the subsonic flow in an arbitrary stream filament of revolution cut by arbitrary turbomachine blades

Description: Report presenting a method to obtain a relatively quick approximate determination of the detailed subsonic flow of a nonviscous fluid past arbitrary turbomachine blades. The method is illustrated with examples of compressible flow in a turbine cascade and in a centrifugal compressor.
Date: June 1952
Creator: Wu, Chung-Hua; Brown, Curtis A. & Prian, Vasily D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Bibliography : Impact Testing of Materials

Description: The bibliography provided investigates the following sources: Chemical Abstracts 1947-1950., Metallurgical Abstracts Vols. 1-18., ASM Review of Metals Literature Vols. 1-6., J. Institute of Metals Vols. 78-80 (No. 7)., Physics Abstracts 1937-1950.
Date: June 8, 1952
Creator: Fick, Jean
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Bismuth Casting and Canning : (Information Report)

Description: Introduction: The experimental work at Mound Laboratory on bismuth casting and the sealing of aluminum irradiation containers is an outgrowth of the bismuth recovery project. Since the recovered bismuth contains residual activity it is necessary that the bismuth be processed to the point that no contamination will result from shipment or any subsequent operations required to prepare the bismuth for irradiation. In order to satisfy these requirements the work here has consisted of investigating … more
Date: June 16, 1952
Creator: Engle, Paul
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Boundary-Layer Measurements on Several Porous Materials With Suction Applied

Description: Memorandum presenting the boundary-layer velocity profiles were measured on ten samples of various porous materials and on impervious aluminum plate mounted flush with the inner surface of the side wall of a small wind tunnel. Suction was applied to the back side of the porous test materials through a 4-inch-square opening. Results regarding measurements on the impervious plate and measurements on porous materials without suction and with suction are provided.
Date: June 18, 1952
Creator: McCullough, George B. & Gambucci, Bruno J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Calculation of lift and pitching moments due to angle of attack and steady pitching velocity at supersonic speeds for thin sweptback tapered wings with streamwise tips and supersonic leading and trailing edges

Description: Report presenting a derivation for a series of thin sweptback tapered wings with streamwise tips and supersonic leading and trailing edges. The results of the analysis are presented as a series of design charts. Results regarding formulas and computations for several derivatives, chordwise center-of-pressure location, and extensions of the results by the use of reversibility theorems are provided.
Date: June 1952
Creator: Martin, John C.; Margolis, Kenneth & Jeffreys, Isabella
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Chordwise pressure distribution at high subsonic speeds near midsemispan of a tapered 35 degree sweptback wing of aspect ratio 4 having NACA 65A006 airfoil sections and equipped with various spoiler ailerons

Description: From Summary: "An investigation was made in the Langley high-speed 7- by 10-foot tunnel through a Mach number range from 0.60 to 0.93 to determine the effects on the chordwise pressure distributions of projecting various spoiler-type ailerons on a swept wing. The semispan 35 degree sweptback wing had an NACA 65A006 airfoil section, an aspect ratio of 4, and a taper ratio of 0.6. The results of the investigation are presented as curves of chordwise pressure distributions near the midspan of the … more
Date: June 24, 1952
Creator: Hammond, Alexander D. & McMullan, Barbara M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Comparison of Three Multicylinder Icing Meters and Critique of Multicylinder Method

Description: "Three multicylinder cloud meters, fundamentally similar but differing in important details, were compared in use at the Mount Washington Observatory. Determinations of liquid water content were found to agree within the limits of the probable error, but the two instruments designed by the National Advisory Committee for Aeronautics indicated larger drop sizes than did the Observatory's instrument, apparently because of spurious ice catch on the rather rough surface of the larger cylinders. Com… more
Date: June 1952
Creator: Howell, Wallace E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Design of apparatus for determining heat transfer and frictional pressure drop of nitric acid flowing through a heated tube

Description: "The object of the research project described herein is to present the design basis for test apparatus to determine the heat-transfer and pressure-drop characteristics of white fuming nitric acid flowing in a heated tube section. The heat flux to the tube will be of the order of magnitude occurring in a regeneratively cooled rocket engine" (p. 1).
Date: June 16, 1952
Creator: Reese, Bruce A. & Graham, Robert W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Displacement Effect of a Three-Dimensional Boundary Layer

Description: Note presenting a method for determining the displacement surface of a known three-dimensional compressible boundary-layer flow in terms of the mass-flow defects associated with the profiles of the two velocity components parallel to the surface. The analysis deals only with the displacement effect of a known boundary layer on the nonviscous outer flow, and can only be applied if the boundary-layer behavior has been determined either theoretically or experimentally.
Date: June 1952
Creator: Moore, Franklin K.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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