You limited your search to:

  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
Feasibility Study, Optimum Natural Uranium, Gas Cooled, Graphite Moderated Nuclear Power Plant for United States Atomic Energy Commission, Idaho Operations Office
Report containing "a discussion of the feasibility design and cost estimates for a gas cooled, natural uranium, graphite moderated power plant optimized for minimum power cost" (p. 3). digital.library.unt.edu/ark:/67531/metadc67253/
Feasibility Study, Optimum Partially Enriched Uranium, Gas Cooled, Graphite Moderated for United States Atomic Energy Commission, Idaho Operations Office
Report that contains "a preliminary design and feasibility studies of gas cooled, graphite moderated, nuclear power plants" (p. 1). digital.library.unt.edu/ark:/67531/metadc67255/
Savannah River Project Site Report: 30,000 KW Prototype Partically Enriched Uranium Gas Cooled, Graphite Moderated Nuclear Power Plant for United States Atomic Energy Commission Idaho Operations Office
Report describing a modified prototype of a nuclear reactor that uses partially uranium-enriched fuel and is cooled by helium. The construction site, site safety aspects, and design and construction costs are included. digital.library.unt.edu/ark:/67531/metadc67311/
Economic Evaluation of a 300 Mwe Fast Supercritical Pressure Power Reactor
Report regarding Hanford Laboratories' 300 Mwe fast supercritical pressure power reactor. This includes descriptions of the plant and reactor, their operations, safety systems, and plant economics. Appendices begin on page 107. digital.library.unt.edu/ark:/67531/metadc100635/
Transportation of Iron Ore, Limestone, and Bituminous Coal on the Great Lakes Waterway System: With Projections to 1995
Report issued by the U.S. Bureau of Mines discussing the transportation of minerals on the Great Lakes Waterway System. As stated in the abstract, "this study provides data on the physical and hydrological makeup of the Great Lakes waterway system and forecasts quantities, traffic patterns, and shipping cost of prospective bulk mineral commerce projected to be transported upon it" (p. 1). This report includes maps, tables, and illustrations. digital.library.unt.edu/ark:/67531/metadc170831/
Optical Mapping of Oak Ridge Research Reactor Experiment Tubes
Report issued by the Oak Ridge National Laboratory discussing optical mapping of experiment tubes. Descriptions of experiment equipment, and designs of the tubes are presented. This report includes tables, illustrations, and photographs. digital.library.unt.edu/ark:/67531/metadc100334/
Aircraft Reactor Test Removal and Disassembly
Report documenting the dissection of a reactor called the Aircraft Reactor Test (ART). Includes the removal of the reactor from its test cell, component removal, and plans for a for a disassembly building facility. digital.library.unt.edu/ark:/67531/metadc100255/
Transonic Flutter Investigation of an All-movable Horizontal Tail for a Fighter Airplane
Transonic flutter of all-movable horizontal tail - bending & pitching moments. digital.library.unt.edu/ark:/67531/metadc52939/
Lift and drag data for 30 pusher-propeller shaft housings on an NACA 65,3-018 airfoil section
No Description digital.library.unt.edu/ark:/67531/metadc61406/
Test of NACA 66,2-116, a = 0.6 airfoil section fitted with pressure balanced and slotted flaps for the wing of the XP-63 airplane
No Description digital.library.unt.edu/ark:/67531/metadc61351/
Experiments with an airfoil model on which the boundary layers are controlled without the use of supplementary equipment
This report describes test made in the Variable Density Wind Tunnel of the NACA to determine the possibility of controlling the boundary layer on the upper surface of an airfoil by use of the low pressure existing near the leading edge. The low pressure was used to induce flow through slots in the upper surface of the wing. The tests showed that the angle of attack for maximum lift was increased at the expense of a reduction in the maximum lift coefficient and an increase in the drag coefficient. digital.library.unt.edu/ark:/67531/metadc54068/
Lift and drag characteristics of a low-drag airfoil with slotted flap submitted by Curtiss-Wright Corporation
No Description digital.library.unt.edu/ark:/67531/metadc61359/
Pressure-distribution measurements of a low-drag airfoil with slotted flap submitted by Curtiss-Wright Corporation
No Description digital.library.unt.edu/ark:/67531/metadc61482/
Preliminary Low-Drag-Airfoil and Flap Data from Tests at Large Reynolds Numbers and Low Turbulence
No Description digital.library.unt.edu/ark:/67531/metadc53121/
Airship model tests in the variable density wind tunnel
This report presents the results of wind tunnel tests conducted to determine the aerodynamic characteristics of airship models. Eight Goodyear-Zeppelin airship models were tested in the original closed-throat tunnel. After the tunnel was rebuilt with an open throat a new model was tested, and one of the Goodyear-Zeppelin models was retested. The results indicate that much may be done to determine the drag of airships from evaluations of the pressure and skin-frictional drags on models tested at large Reynolds number. digital.library.unt.edu/ark:/67531/metadc66051/
The drag of two streamline bodies as affected by protuberances and appendages
This report presents the results of wind tunnel tests of two airship models conducted to determine the drag coefficients at zero pitch, and the effect of fins and cars and of flat and streamlined protuberances located at various positions along the hull. During the investigation the stern of one model was rounded off to produce a blunter shape. The extreme range of the Reynolds number based on the over-all length of the models was from 1,300,000 to 33,000,000. At large values of the Reynolds number the streamlined protuberance affected the drag very little, and the additional drag caused by the flat protuberance was less than the calculated drag by the protuberance alone. The fins and cars together increased the bare-hull drag about 20 per cent. digital.library.unt.edu/ark:/67531/metadc66109/
Flow observations with tufts and lampblack of the stalling of four typical airfoil sections in the NACA variable-density tunnel
A preliminary investigation of the stalling processes of four typical airfoil sections was made over the critical range of the Reynolds Number. Motion pictures were taken of the movements of small silk tufts on the airfoil surface as the angle of attack increased through a range of angles including the stall. The boundary-layer flow also at certain angles of attack was indicated by the patterns formed by a suspension of lampblack in oil brushed onto the airfoil surface. These observations were analyzed together with corresponding force-test measurements to derive a picture of the stalling processes of airfoils. digital.library.unt.edu/ark:/67531/metadc54487/
Fuselage-drag tests in the variable-density wind tunnel: streamline bodies of revolution, fineness ratio of 5
Results are presented of the drag tests of six bodies of revolution with systematically varying shapes and with a fineness ratio of 5. The forms were derived from source-sink distributions, and formulas are presented for the calculation of the pressure distribution of the forms. The tests were made in the N.A.C.A. variable-density tunnel over a range of values of Reynolds number from about 1,500,000 to 25,000,000. The results show that the bodies with the sharper noses and tails have the lowest drag coefficients, even when the drag coefficients are based on the two-thirds power of the volume. The data shows the most important single characteristic of the body form to be the tail angle, which must be fine to obtain low drag. digital.library.unt.edu/ark:/67531/metadc54304/
Interference effects of longitudinal flat plates on low-drag airfoils
No Description digital.library.unt.edu/ark:/67531/metadc61370/
Pressure-Distribution Measurements of a Model of a Davis Wing Section with Fowler Flap Submitted by Consolidated Aircraft Corporation
Wing pressure distribution diagrams for several angles of attack and flap deflections of 0 degrees, 20 degrees, and 40 degrees are presented. The normal force coefficients agree with lift coefficients obtained in previous test of the same model, except for the maximum lifts with flap deflection. Pressure distribution measurements were made at Reynolds Number of about 6,000,000. digital.library.unt.edu/ark:/67531/metadc61480/
Pressure-distribution measurements of two airfoil models with Fowler flaps submitted by Consolidated Aircraft Corporation as alternative wing sections of the XB-32 airplane
No Description digital.library.unt.edu/ark:/67531/metadc61481/
Summary of Airfoil Data
The historical development of NACA airfoils is briefly reviewed. New data are presented that permit the rapid calculation of the approximate pressure distributions for the older NACA four-digit and five-digit airfoils by the same methods used for the NACA 6-series airfoils. The general methods used to derive the basic thickness forms for NACA 6 and 7-series airfoils together with their corresponding pressure distributions are presented. Detail data necessary for the application of the airfoils to wing design are presented in supplementary figures placed at the end of the paper. The report includes an analysis of the lift, drag, pitching-moment, and critical-speed characteristics of the airfoils, together with a discussion of the effects of surface conditions. Available data on high-lift devices are presented. Problems associated with lateral-control devices, leading-edge air intakes, and interference are briefly discussed, together with aerodynamic problems of application. (author). digital.library.unt.edu/ark:/67531/metadc65534/
Tests in the variable-density wind tunnel of the NACA 23012 airfoil with plain and split flaps
Section characteristics for use in wing design are presented for the NACA 23012 airfoil with plain and split flaps of 20 percent wing chord at a value of the effective Reynolds number of about 8,000,000. The flap deflections covered a range from 60 degrees upward to 75 degrees downward for the plain flap and from neutral to 90 degrees downward for the split flap. The split flap was aerodynamically superior to the plain flap in producing high maximum lift coefficients and in having lower profile-drag coefficients at high lift coefficients. digital.library.unt.edu/ark:/67531/metadc66319/
Tests of four models representing intermediate sections of the XB-33 airplane including sections with slotted flap and ailerons
No Description digital.library.unt.edu/ark:/67531/metadc61366/
Tests of a Highly Cambered Low-Drag-Airfoil Section with a Lift-Control Flap, Special Report
Tests were made in the NACA two-dimensional low turbulence pressure tunnel of a highly cambered low-drag airfoil (NACA 65,3-618) with a plain flap designed for lift control. The results indicate that such a combination offers attractive possibilities for obtaining low profile-drag coefficients over a wide range of lift coefficients without large reductions of critical speed. digital.library.unt.edu/ark:/67531/metadc65162/
Tail Buffeting
An approximate theory of buffeting is here presented, based on the assumption of harmonic disturbing forces. Two cases of buffeting are considered: namely, for a tail angle of attack greater and less than the stalling angle, respectively. On the basis of the tests conducted and the results of foreign investigators, a general analysis is given of the nature of the forced vibrations the possible load limits on the tail, and the methods of elimination of buffeting. digital.library.unt.edu/ark:/67531/metadc64651/
The Theory of a Free Jet of a Compressible Gas
In the present report the theory of free turbulence propagation and the boundary layer theory are developed for a plane-parallel free stream of a compressible fluid. In constructing the theory use was made of the turbulence hypothesis by Taylor (transport of vorticity) which gives best agreement with test results for problems involving heat transfer in free jets. digital.library.unt.edu/ark:/67531/metadc64427/
Theoretical Investigation of the Performance of Proportional Navigation Guidance Systems-effect of Method of Positioning the Radar Antenna on the Speed of Response
Proportional navigation guidance systems - radar antenna positioning effects on speed of response. digital.library.unt.edu/ark:/67531/metadc52867/
The effect of stick-force gradient and stick gearing on the tracking accuracy of a fighter airplane
No Description digital.library.unt.edu/ark:/67531/metadc60967/
Investigation of the use of a stick force proportional to pitching acceleration for normal-acceleration warning
No Description digital.library.unt.edu/ark:/67531/metadc59608/
Theoretical Investigation of the Effects of the Artificial-Feel System on the Maneuvering Characteristics of the F-89 Airplane
The possibility of overshooting the anticipated normal acceleration as a result of the artificial-feel characteristics of the F-89C airplane at a condition of minimum static stability was investigated analytically by means of an electronic simulator. Several methods of improving the stick-force characteristics were studied. It is shown that, due to the lag in build-up of the portion of the stick force introduced by the bobweight, it would be possible for excessive overshoots of normal acceleration to occur in abrupt maneuvers with reasonable assumed control movements. The addition of a transient stick force proportional to pitching acceleration (which leads the normal acceleration) to prevent this occurring would not be practical due to the introduction of an oscillatory mode to the stick-position response. A device to introduce a viscous damping force would Improve the stick-force characteristics so that normal acceleration overshoots would not be likely, and the variation of the maximum stick force in rapid pulse-type maneuvers with duration of the maneuver then would have a favorable trend. digital.library.unt.edu/ark:/67531/metadc65491/
Theoretical investigation of the performance of proportional navigation guidance systems : effect of method of positioning the radar antenna on the speed of response
No Description digital.library.unt.edu/ark:/67531/metadc59356/
Theoretical investigation of the performance of proportional navigation guidance systems : effect of missile configuration on the speed of response
No Description digital.library.unt.edu/ark:/67531/metadc64700/
Handbook of Mathematical Functions With Formulas, Graphs, and Mathematical Tables
No Description digital.library.unt.edu/ark:/67531/metadc40302/
Handbook of Mathematical Functions With Formulas, Graphs, and Mathematical Tables
No Description digital.library.unt.edu/ark:/67531/metadc40301/
Investigation of internal film cooling of exhaust nozzle of a 1000-pound-thrust liquid-ammonia liquid-oxygen rocket
No Description digital.library.unt.edu/ark:/67531/metadc59313/
Variation in the number of revolutions of air propellers
No Description digital.library.unt.edu/ark:/67531/metadc53827/
Flight investigation of a liquid hydrogen fuel system
No Description digital.library.unt.edu/ark:/67531/metadc53242/
Natural icing of an axial-flow turbojet engine in flight for a single icing condition
No Description digital.library.unt.edu/ark:/67531/metadc53462/
Preliminary results of natural icing of an axial-flow turbojet engine
No Description digital.library.unt.edu/ark:/67531/metadc53464/
Accelerations in fighter-airplane crashes
No Description digital.library.unt.edu/ark:/67531/metadc63594/
Comparison of flight performance of AN-F-58 and AN-F-32 fuels in J35 turbojet engine
No Description digital.library.unt.edu/ark:/67531/metadc57982/
Effects of inlet icing on performance of axial-flow turbojet engine in natural icing conditions
A flight investigation in natural icing conditions was conducted to determine the effect of inlet ice formations on the performance of axial-flow turbojet engines. The results are presented for icing conditions ranging from a liquid-water content of 0.1 to 0.9 gram per cubic meter and water-droplet size from 10 to 27 microns at ambient-air temperature from 13 to 26 degrees F. The data show time histories of jet thrust, air flow, tail-pipe temperature, compressor efficiency, and icing parameters for each icing encounter. The effect of inlet-guide-vane icing was isolated and shown to account for approximately one-half the total reduction in performance caused by inlet icing. digital.library.unt.edu/ark:/67531/metadc58470/
Preliminary results of natural icing of an axial-flow turbojet engine
No Description digital.library.unt.edu/ark:/67531/metadc57582/
Flight Comparison of Performance and Cooling Characteristics of Exhaust-Ejector Installation with Exhaust-Collector-Ring Installation
Flight and ground investigations have been made to compare an exhaust-ejector installation with a standard exhaust-collector-ring installation on air-cooled aircraft engines in a twin-engine airplane. The ground investigation allowed that, whereas the standard engine would have overheated above 600 horsepower, the engine with exhaust ejectors cooled at take-off operating conditions at zero ram. The exhaust ejectors provided as much cooling with cowl flaps closed as the conventional cowl flaps induced when full open at low airspeeds. The propulsive thrust of the exhaust-ejector installation was calculated to be slightly less than the thrust of the collector-ring-installation. digital.library.unt.edu/ark:/67531/metadc63773/
Air forces on airfoils moving faster than sound
We are undertaking the task of computing the air forces on a slightly cambered airfoil in the absence of friction and with an infinite aspect ratio. We also assume in advance that the leading edge is very sharp and that its tangent lies in the direction of motion. digital.library.unt.edu/ark:/67531/metadc59216/
Drag measurements of two thin wing sections at different index values
It is stated that the index value 6000, as found in normal tests of wing sections with a 20 cm chord, falls in the same region where the transition of laminar to turbulent flow takes place on thin flat plates. It is to be expected that slightly cambered, thin wing sections will behave similarly. The following test of two such wing sections were made for the purpose of verifying this supposition. digital.library.unt.edu/ark:/67531/metadc65241/
Experiments on airfoils with trailing edge cut away
Airfoils with their trailing edge cut away are often found on aircraft, as the fins on the hulls of flying boats and the central section of the wings for affording better visibility. It was therefore of some interest to discover the effect of such cutaways on the lift and drag and on the position of the center of pressure. For this purpose, systematic experiments were performed on two different airfoils, a symmetrical airfoil and an airfoil of medium thickness, with successive shortenings of their chords. digital.library.unt.edu/ark:/67531/metadc65246/
Experiments with an airfoil from which the boundary layer is removed by suction
Our attempts to improve the properties of airfoils by removing the boundary layer by suction, go back to 1922. The object of the suction is chiefly to prevent the detachment of the boundary layer from the surface of the airfoil. At large angles of attack, such detachment prevents the attainment of the great lift promised by the theory, besides greatly increasing the drag, especially of thick airfoils. This report gives results of those experiments. digital.library.unt.edu/ark:/67531/metadc65081/
High-speed wind tunnels
Wind tunnel construction and design is discussed especially in relation to subsonic and supersonic speeds. Reynolds Numbers and the theory of compressible flows are also taken into consideration in designing new tunnels. digital.library.unt.edu/ark:/67531/metadc63396/
FIRST PREV 1 2 3 4 5 NEXT LAST