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Results of Primary Triangulation and Primary Traverse: fiscal year 1903-04
From introduction: This report contains the results of primary triangulation and primary traverse in the eastern and western divisions of the United States.
Results of recent experiments with slotted wings
This report gives the results of a recent series of experiments performed on a wing designed for a cantilever monoplane. Both wings were trapezial in their ground plan, with their tips rounded elliptically. These wing sections combine all known devices for increasing the lift, namely, the slot, the increased camber and angle of attack by means of an aileron running the whole length of the span. The last advance included in the wing section was an increase in wing area by means of an auxiliary wing adjusted by a sort of rectangular joint.
Results of rocket model test of an airplane configuration having an arrow wing and slender flat-sided fuselage : lift, drag, longitudinal stability, lateral force, and jet effects at Mach numbers between 1.0 and 2.3
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Results of shear fatigue tests of joints with 3/16-inch-diameter 24S-T31 rivets in 0.064-inch-thick alclad sheet
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Results of tests on radiators for aircraft engines
Part 1 is to present the results of tests on 56 types of core in a form convenient for use in the study of the performance of and possible improvements in existing designs. Working rules are given by which the data contained in the report may be used, and the most obvious conclusions as to the behavior of cores are summarized. Part 2 presents the results of tests made to determine the pressure necessary to produce water flows up to 50 gallons per minute through an 8-inch square section of radiator core. These data are of special value in evaluating the hydraulic head against which the circulating pump is required to operate.
Results of Tests to Determine the Effect of a Conical Windshield on the Drag of a Bluff Body at Supersonic Speeds
Tests to evaluate the effect of a conical windshield on the drag of a bluff body at supersonic speeds were performed for the following configurations: a sharp nose fuselage with stabilizing fins,a blunt nose fuselage with a hemispherical shape, and a blunt nose fuselage with a conical point. Results of the drag coeeficient are described at Mach 1.0 and the greatest Mach number of 1.37.
Results of the flight test of a 0.13-scale rocket-boosted model of the McDonnell F4H-1 airplane between Mach numbers of 0.20 and 1.90
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Results of the flight test of a 0.13-scale rocket-boosted model of the McDonnell F4H-1 airplane between Mach numbers of 0.20 and 1.90 : TED No. NACA AD 3115
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Results of the Flight Test of a Dummy of the MX-656 Rocket-Propelled Models
The data obtained from the flight of a simplified (dummy) rocket-propelled model of the MX-656 have been analyzed to determine the booster-model characteristics and the model-alone characteristics up to a Mach number of 1.3. The data indicate that the model-booster combination is satisfactory. The model alone is longitudinally stable i n the Mach number range covered by the test (0.9 to 1.3) with the center of gravity at -15 percent of the mean aerodynamic chord. With the stabilizer setting at 0 deg. the variation of normal-force coefficient with Mach number is not large. The total-drag-coefficient variation with Mach number is not unusual. About 12 percent of the total drag at a Mach number of 1.3 can be attributed to body base drag.
Results of two free-fall experiments on flutter of thin unswept wings in the transonic speed range
Results of four thin, unswept, flutter airfoils attached to two freely falling bodies are reported. Two airfoils fluttered at a Mach number of 0.85, a third airfoil fluttered at a Mach number of 1.03, and a fourth fluttered at a Mach number of 1.07. Results of calculations of flutter speed using incompressible and compressible air-force coefficients, including a Mach number of 1.0, are presented.
Results of UO₂ Diagnositic Tests for Run Beyond Cladding Breach in EBR-2
Pre-defected uranium dioxide fuel elements were irradiated in EBR-II to determine the response of the fission-product-monitoring systems. In particular, the tests were performed to indicate whether the amount of oxide fuel exposed to the primary sodium could be estimated by monitoring, with the fuel-element-rupture detector (FERD), delayed neutrons (DN's) emitted from bromine and iodine isotopes in the sodium. Elements with defect areas of 0.005 and 0.20 cm sq. were irradiated consecutively in April and June 1977. Post-irradiation examination of the elements showed that an unexpectedly large amount of uranium dioxide/sodium chemical reaction occurred in the element with the 0.20-cm sq. defect.
The results of wind-tunnel tests at low speeds of a four-engine propeller-driven airplane configuration having a wing with 40 degrees of sweepback and an aspect ratio of 10
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The results of wind-tunnel tests to a Mach number of 0.90 of a four-engine, propeller-driven airplane configuration having a wing with 40 degrees of sweepback and an aspect ratio of 10
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Resume and analysis of NACA lateral control research
An analysis of the principal results of recent NACA lateral control research is made by utilizing the experience and progress gained during the course of the investigation. Two things are considered of primary importance in judging the effectiveness of different control devices: the (calculated) banking and yawing motion of a typical small airplane caused by a deflection of the control, and the stick force required to produce this deflection. The report includes a table in which a number of different lateral control devices are compared on these bases.
Resume of air-load data on slats and flaps
A resume of the generally available test data regarding air loads on slats and flaps is presented and data attained up to the fall of 1938 are included. The data are given in the form of N.A.C.A. standard coefficients of air forces and moments on the lift-increasing device and, when available, the aerodynamic characteristics of the combined wing and high-lift device are included. Slats of the Handley Page type, fixed auxiliary airfoils, and flaps of several different types are covered.
Resume of hinge-moment data for unshielded horn- balanced control surfaces
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Resume of NACA stability and control tests of the Bell P-63 series airplane
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Resume of Present Data on Load Distribution on Slots and Flaps, Special Report
This report covers a study of the generally available data on load distribution on slots and flaps. The study was made by the National Advisory Committee for Aeronautics at the request of the Material Division, Army Air Corps to furnish information applicable to design criteria for slots and flaps of various types. The data are presented in three main sections: slots (Handley page type), auxiliary airfoils (fixed), and flaps.
Resume of Producer-Gas Investigations: October 1, 1904-June 30, 1910
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Resume of the activities of the Aeronautical Experimental Institute, Rome, during the months of May, June, July and August 1921
This report is a listing of the different studies conducted by the Institute in May thru August of 1921. The aerodynamical section studied: the aerodynamical characteristics of a very thick concave-convex wing; the disturbance caused in a tunnel by the presence of a disk, placed in relation with a transversely infinite barrier; vertical pressure in a wing of low head resistance; the drag caused by two small doors in the sides of the fuselage. Some other studies conducted by the Institute included: depressions in the interior of the model of a wing; the influence of a conical casing fitted with helicoidal flanges centered on the hub of the propeller; the influence of the velocity of translation on the aerodynamical effects of the propeller; and the influence of a honeycomb placed in the tunnel.
A resume of the advances in theoretical aeronautics made by Max M. Munk
In order to apply profitably the mathematical methods of hydrodynamics to aeronautical problems, it is necessary to make simplifications in the physical conditions of the latter. To begin with, it is allowable in many problems, as Prandtl has so successfully shown, to treat the air as having constant density and as free of viscosity. But this is not sufficient. It is also necessary to specify certain shapes for the solid bodies whose motion through the air is discussed, shapes suggested by the actual solids - airships or airfoils - it is true, but so chosen that they lead to solvable problems. In a valuable paper presented by Dr. Max M. Munk, of the National Advisory Committee for Aeronautics, Washington, to the Delft Conference in April, 1924, these necessary simplifying assumptions are discussed in detail. It is the purpose of the present paper to present in as simple a manner as possible some of the interesting results obtained by Dr. Munk's methods.
Resume of the theory of naval and aerial propulsive propellers and of airplanes in the rectilinear flight
Though dissimilar, these two subjects have been united because they have some points in common. The computation of the movement of an airplane can only be correctly established if we are in a position to know exactly the thrust and resisting torque of the propeller for the various values of slip, which may vary greatly according to circumstance. The first part of the work concerns propellers and introduces as a fundamental variable, the true slip (delta) with respect to the effective pitch, which is the advance per revolution of the propeller corresponding to no thrust. The second part deals with characteristic curves of an airplane.
Resume of wind-tunnel data on the effect of external stores on stability of models of military airplanes
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Retrogressive Failures in Sand Deposits of the Mississippi River, Report 1: Field Investigations, Laboratory Studies and Analysis of the Hypothesized Failure Mechanism
First report regarding geotechnical field investigations meant to apply current state-of-the-art knowledge and methods to assessing the in situ characteristics of susceptible point bar deposits below Baton Rouge.
Retrogressive Failures in Sand Deposits of the Mississippi River, Report 2: Empirical Evidence in Support of the Hypothesized Failure Mechanism and Development of the Levee Safety Flow Slide Monitoring System
This report represents a continuation of efforts by the Lower Mississippi Valley Division (LMVD), US Army Corps of Engineers, to develop an effective plan for and means of protecting the integrity of main line Mississippi River levees from the threat of flow slides in sand deposits.
Reuse and Subsurface Injection of Municipal Sewage Effluent: Two Case Histories
Report issued by the U.S. Bureau of Mines discussing sewage disposal and reuse. As stated in the introduction, "this paper describes the renovation of municipal sewage water for industrial use, and the use of subsurface waste disposal by an industrial complex and by a city" (p. 1). This report includes tables, and illustrations.
Reverse Osmosis for Water Desalination
Report issued by the Office of Saline Water over studies conducted on the reverse-osmosis program. The methods of desalination through osmosis are discussed. This report includes tables, illustrations, and photographs.
The reversibility theorem for thin airfoils in subsonic and supersonic flow
A method introduced by Munk is extended to prove that the light-curve slope of thin wings in either subsonic flow or supersonic flow is the same when the direction of flight of the wing is reversed. It is also shown that the wing reversal does not change the thickness drag, damping-in-roll parameter or the damping-in-pitch parameter.
A Review and Analysis of Fortran 8x
The ANSI Standards Subcommittee X3J3 on Fortran has recently completed a draft proposed standard for the Fortran programming language. The draft proposed standard, known informally as Fortran 8x, is a revision of the current standard X3.9-1978, known informally as Fortran 77. This report is a review of Fortran 8x and consists of a series of six articles. The first article gives a general overview of Fortran 8x. The next three articles give brief discussions of the array facilities; the enhanced numeric facilities; and user-defined data types, procedure interfaces, and the new program unit called a module. The fifth article provides a brief analysis of the controversial issues discussed by X3J3 (including both the accepted and rejected facilities for Fortran 8x). The sixth article gives a brief comparison with Ada. The report concludes with a summary giving information on how and where to express opinions of the draft proposed standard.
Review and Analysis of Spray Combustion as Related to Alternative Fuels
A review was conducted during the period of mid-June to mid-August 1979, of the literature on spray combustion. Particular attention has been paid to theoretical and experimental work on droplet and spray combustion applicable to the use of alternate fuels, mainly liquid fuels derived from coal and shale.
Review and Evaluation of Extractants for Strontium Removal Using Magnetically Assisted Chemical Separation
A literature review on extractants for strontium removal was initially performed at Northern Illinois University to assess their potential in magnetically assisted chemical separation. A series of potential strontium extractants was systematically evaluated there using radioanalytical methods. Initial experiments were designed to test the uptake of strontium from nitric acid using several samples of magnetic extractant particles that were coated with various crown ether ligands. High partition coefficient (K(sub d)) values for stimulant tank waste were obtained. Further studies demonstrated that the large partitioning was due to uncoated particles.
Review and investigation of unsatisfactory control characteristics involving in stability of pilot-airplane combination and methods for predicting these difficulties from ground tests
A number of examples are presented of control difficulties not completely covered by existing handling-qualities requirements. 520/3:*:These control difficulties appear to result from a tendency for dynamic instability of the combination of pilot, control system, and airplane. The unsatisfactory characteristics involved have been encountered most frequently with hydraulic-power control systems. The nature of the difficulties may range from a slight interference with the ability of the pilot to hold precisely straight and level flight to a dangerous tendency toward divergent short-period oscillations which require constant attention of the pilot to control. Tests of a bomber and a fighter airplane with experimental power control systems have been made to study this problem further. The results of the investigation show that control difficulties of the type considered have always been associated with a marked phase difference between the pilot's control force and the associated control-surface deflection. The presence of static friction in the control valves of hydraulic-power control systems was found to be the explanation for unsatisfactory characteristics in several airplanes equipped with such systems. The valve friction may cause a phase lag between the pilot's control force and the associated control-surface deflection approaching 180 degrees at small control deflections. Definite limits or simple rules for the tolerable amount of valve friction appear to be difficult to establish because of the large number of variables which may influence the problem.The control characteristics of the airplanes tested were strongly influenced by minor design details of the power control systems.
Review and investigation of unsatisfactory control characteristics involving instability of pilot-airplane combination and methods for predicting these difficulties from ground tests
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Review of an Investigation of Ceramic Coatings for Metallic Turbine Parts and Other High-Temperature Applications
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A review of boundary-layer literature
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Review of current and anticipated lubricant problems in turbojet engines
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A Review of Degradation Behavior of Container Materials for Disposal of High-Level Nuclear Waste in Tuff and Alternative Repository Environments
Corrosion resistance of materials in aqueous systems is reviewed from the perspective of their suitability as container materials for nuclear waste. A discussion of the chemistry and characterization of repository environments, namely, tuff and alternative environments (shale, limestone, and carbonate), is followed by a description of corrosion mechanisms. In this review, emphasis is placed on localized corrosion (e.g., stress corrosion cracking, crevice corrosion, and pitting) because localized corrosion is difficult to account for in design of components, but it is the life-limiting factor for many metallic and nonmetallic systems.
A Review of Dynamic Characteristics of Magnetically Levitated Vehicle Systems
The dynamic response of magnetically levitated (maglev) ground transportation systems has important consequences for safety and ride quality, guideway design, and system costs. Ride quality is determined by vehicle response and by environmental factors such as humidity and noise. The dynamic response of the vehicles is the key element in determining ride quality, while vehicle stability is an important safety-related element. To design a guideway that provides acceptable ride quality in the stable region, vehicle dynamics must be understood. Furthermore, the trade-off between guideway smoothness and levitation and control systems must be considered if maglev systems are to be economically feasible. The link between the guideway and the other maglev components is vehicle dynamics. For a commercial maglev system, vehicle dynamics must be analyzed and tested in detail. This report, which reviews various aspects of the dynamic characteristics, experiments and analysis, and design guidelines for maglev systems, discusses vehicle stability, motion dependent magnetic force components, guideway characteristics, vehicle/ guideway interaction, ride quality, suspension control laws, aerodynamic loads and other excitations, and research needs.
Review of Experimental Investigations of Liquid-Metal Heat Transfer
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Review of experimental investigations of liquid-metal heat transfer
Experimental data of various investigators of liquid-metal heat-transfer characteristics were reevaluated using as consistent assumptions and methods as possible and then compared with each other and with theoretical results. The reevaluated data for both local fully developed and average Nusselt numbers in the turbulent flow region were found still to have considerable spread, with the bulk of the data being lower than predicted by existing analysis. An equation based on empirical grounds which represents most of the fully developed heat-transfer data is nu = 0.625 pe(0.4) where nu represents the Nusselt number and pe the Peclet number. The theoretical prediction of the heat transfer in the entrance region was found to give lower values, in most cases, than those found in the experimental work.
Review of flight tests of NACA C and D cowlings on the XP-42 airplane
Results of flight tests of the performance and cooling characteristics of three NACA D cowlings and of a conventional NACA D cowling on the XP-42 airplane are summarized and compared. The D cowling is, in general, characterized by the use of an annular inlet and diffuser section for the engine-cooling air. The D cowlings tested were a long-nose high-inlet-velocity cowling, a short-nose high-inlet-velocity cowling, and a short-nose low inlet-velocity cowling. The use of wide-chord propeller cuffs or an axial-flow fan with the D cowlings increased the cooling pressure recoveries in the climb condition at the expense of some of the improvement in speed.
Review of flight tests of NACA C and D cowlings on the XP-42 airplane
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Review of high-performance axial-flow-compressor blade-element theory
This report presents a review of current compressor blade-element theory with particular emphasis on application to the transonic high-performance compressor. A discussion of the significant parameters of total-pressure loss and deviation angle is presented, and an indication of the extent of available knowledge and the problems involved in the determination of blade-element characteristics is given. Some recent results and considerations in this pursuit and suggestions for further avenues of investigation are indicated.
Review of information on induced flow of a lifting rotor
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A review of information on the mechanical properties of aluminum alloys at low temperatures
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A review of instruments developed for the measurement of the meteorological factors conductive to aircraft icing
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A Review of Leakage-Flow-Induced Vibrations of Reactor Components
The primary-coolant flow paths of a reactor system are usually subject to close scrutiny in a design review to identify potential flow-induced vibration sources. However, secondary-flow paths through narrow gaps in component supports, which parallel the primary-flow path, occasionally are the excitation source for significant vibrations even though the secondary-flow rates are orders of magnitude smaller than the primary-flow rate. These so-called leakage flow problems are reviewed here to identify design features and excitation sources that should be avoided. Also, design rules of thumb are formulated that can be employed to guide a design, but quantitative prediction of component response is found to require scale-model testing.
Review of Literature on Dusts
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Review of Literature on Effects of Breathing Dusts with Special Reference to Silicosis
From Introduction: "This bulletin is an attempt to assemble information in convenient form on effects of breathing dusts, largely in the mining and allied industries. The literature on this subject is so extensive that no attempt has been made to include all published material or all types of dust disease but only to assemble some of the more outstanding data on several aspects of the subject, especially with reference to silicosis."
Review of literature pertinent to fire-extinguishing agents and to basic mechanisms involved in their action
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