Technical Report Archive & Image Library (TRAIL) - 116 Matching Results
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- Additional Experiments With Flat-Top Wing- Body Combinations at High Supersonic Speeds
- Memorandum presenting an experimental study of the effects of several variations in configuration geometry on the aerodynamic characteristics of flat-top wing-body combinations. Generally, the configurations consist of one half of a body of revolution mounted beneath a wing of essentially arrow plan form. Results regarding the effect of trailing-edge sweep, effect of the addition of auxiliary bodies, effect of tip-flap deflection, effect of dihedral, effect of leading-edge sweep, effect of fuselage fineness ratio, effect of fuselage profile shape, and static longitudinal stability characteristics are provided.
- Altitude performance of a full-scale turbojet engine using pentaborane fuels
- From Introduction: "The data presented herein include the standard engine performance parameters of net thrust, specific fuel consumption, and engine total-pressure ratio that reflect the performance available from the use of pentaborane as a fuel. The influence of the boric oxide deposits from the high-concentration pentaborane fuels on engine component performance is presented."
- An analog computer study of several stability augmentation schemes designed to alleviate roll-induced instability
- From Introduction: "The purpose of the present study is to investigate these suggested methods for reducing the undesirable pitching and yawing motions of an airplane during roll maneuvers. The airplane characteristics used in this study were those of the F-100A airplane having the original small vertical tail as shown in figure 1."
- Analytical and experimental investigation of the effects of compressor interstage air bleed on performance characteristics of a 13-stage axial-flow compressor
- Air was bled over the fifth-and tenth-stage rotor-blade rows through ports designed to pass 11 and 9 percent of the inlet flow, respectively, at 80 percent speed. Along the rated operating line the maximum speed at which rotating stall was encountered was lowered by either of these bleeds, and the stall patterns below these speeds were altered so that no dangerous resonant rotor-blade bending vibrations were excited. The combination of the two bleeds completely eliminated rotating stall to at least 50 percent speed. The compressor-discharge weight flow was decreased only at intermediate speeds, and the overall pressure ratio was affected only at intermediate speeds, and the overall pressure ratio was affected only by the combination bleed at intermediate speeds. Fifth-stage bleed increased compressor efficiency at low speeds, and tenth-stage bleed decreased efficiency at intermediate speeds.
- Approximate solution for streamlines about a lifting rotor having uniform loading and operating in hovering or low-speed vertical-ascent flight conditions
- Report presenting that the usual assumption of a uniform vortex cylinder for the wake vortex structure of a uniformly loaded, lifting rotor operating in the hovering or low-speed vertical-ascent flight conditions does not yield useful results for induced velocities in the region about the periphery of the rotor.
- Beehive and Hornet : Reactor Codes for Spherical Geometry
- Abstract: Beehive is a five energy group, two region, time independent spherical reactor code. It considers the problem of reactor system in which the core material is assumed to be at a higher energy (temperature) than the reflector material. The code obtains a closed solution for the critical reactor assembly by a procedure which is a logical extension of normal two group theory. The companion code, Hornet, computes the neutron fluxes for the critical assembly determined by the Beehive calculation. Both codes have been programmed for the IBM Magnetic Drum Data-Processing Machine, Type 650. The codes, together with the flow diagrams, are included with this report.
- Bellows Failure in Solids Separation Loop of the HRT Mockup
- The failure of the valve bellows would appear to be due to a combination of stress corrosion and crevice corrosion. Stress corrosion occurred as evidenced by the transgranular branched cracking found in the bellows and in the base which which was joined to the bellows. It seems probable that chlorides were present, which, along with the residual stresses present in the bellows assembly, created the necessary conditions for stress corrosion to occur. Crevice corrosion occurred probably due to heavy deposits of solids at the base of the bellows, which created a condition of oxygen impoverishment. While the crater in the base may have been related to a galvanic effect created by the gold gasket, the contour of the crater would suggest that the cause of the crater was due more to crevice corrosion.
- Beneficiation of Iron-Copper Ores from Kasaan Peninsula, Prince of Wales Island, Alaska
- Report issued by the Bureau of Mines over studies conducted on the beneficiation of iron-copper ores. As stated in the summary, "this report summarizes the results of laboratory testing of copper-bearing magnetite ore from the Poorman, Rush and Brown, and Copper Center deposits, Kasaan Peninsula, Prince of Wales Island, southeastern Alaska" (p. 1). This report includes tables, maps, and illustrations.
- A Brief Review of thermal Gradient Mass Transfer in Sodium and NaK Systems
- The fact that material transport does occur under conditions of finite temperature difference in a flowing molten metal system was established. The rate mass transfer was thought to be either diffusion limited or solution rate limited. It is believed that the mass transfer of structural materials in Na or NaK systems is solution rate limited. The limiting process has not been qualitatively or quantitatively confirmed for the Inconel-Na or Inconel-NaK system. Increasing the maximum system wall temperature increases the amount of mass transfer, at least above 1300 deg F. The effect of the total temperature difference across the system on the amount of mass transfer was determined.
- Calculation of Wall-Scattered Gamma Radiation Escaping through a Shield Opening - Application to the HRT
- A simplified method was developed for calculating wall-scatter gamma radiation escaping through a shield opening. The method was applied to the HRT and the results showed that next to the line of sight contribution, scattering of the wall of the shield opening was the main contribution to the dose at the rear edge of the shield. Design charts were prepared that give the dose as a function of the gamma source location with the reactor cell.
- Capillary Flowmeter
- The HRT leak detector system consists of four headers each of which are connected on one side to a common supply of pressurized water and on the other side by individual tubing to the ring grooves of approximately twenty flanges. There are two methods of detecting the loss of water that are particularly applicable to the HRT: (1) By the loss of pressure in a constant volume system; (2) By the measurement of flow from a constant pressure system. It was determined to investigate the second method which requires a flowmeter capable of measuring flows of .5 cc or less of water per hour. The experiment flowmeter constructed performed almost exactly as the design calculations predicted.
- Characteristics and Analyses of Ninety-Two Colorado Crude Oils
- Report issued by the Bureau of Mines over the characteristics and properties of many different crude-oil samples from Colorado. The properties of each sample are presented. This report includes table, maps, and illustrations.
- Comparison of Combustion Reactivity of Ethyldecaborane Fuels With Typical Hydrocarbon Fuels on Basis of Spray Flammability Limits of Fuel-Rich Mists and Calculated Lean-Limit Flame Temperatures for Fuel Vapor-Air Systems
- From Summary: "The spray flammability limits of various high-energy fuels and hydrocarbon fuels were determined experimentally in an apparatus which measured the minimum percent of oxygen by volume that would permit the ignition of a particular fuel. The fluids investigated were ethyldecaboranes, aliphatic hydrocarbons, olefins, aromatic hydrocarbons, and esters."
- Comparison of the Combustion Performance of Shell UMF, Grade C, MIL-F-5624C, Grade JP-5, Fuels in a Heavy-Duty XRJ47-W-9 Ram-Jet Engine
- Comparable combustion performance data for Shell UMF, grade C, and MIL-F-5624C, grade JP-5, fuels were obtained using a heavy-duty version of the XRJ47-W-9 ram-jet engine operated in a 2.75 Mach number free-jet facility. Data were obtained for the two fuels over a range of fuel-air ratios, engine airflows, and engine-inlet temperatures. The test conditions were selected to provide combustor-inlet temperatures. The test conditions were selected to provide combustor-inlet conditions approximately representative of those which would be encountered over a range of altitudes and flight Mach numbers. The variation of combustion efficiency with fuel-air ratio for the two fuels is compared at the several inlet conditions. The pilot-burner ignition and operating limits with both fuels are also included. In general, the combustion efficiency with Shell UMF, grade C, fuel was 1 to 4 points lower than with MIL-F-5624C, grade JP-5, fuel.
- Control System for HRT Cooling Water
- The circuits described herein and shown functionally in Fig. 1 are to be added to the HRT control circuit to provide control and protection for the revised HRT cooling water system. The circuitry will provide protection against excess pressure in the demineralized cooling water loop and cooling water activity, will initiate action to insure containment of activity in event of an explosion and will provide emergency cooling water from the tower basin when required.
- A Description of a Shock Wave in Free Particle Hydrodynamics with Internal Magnetic Fields
- Abstract: "The structure of an extremely strong magnetohydrodynamic shock is discussed in the limit of no particle collisions. It is tentatively concluded that the shock transition takes place through the mechanism of a strong electric field produced by charge separation. The pressure in the shocked plasma is due primarily to a very high electron temperature. The ions, on the other hand, undergo an irreversible temperature change of only 3."
- Design and test of mixed-flow impellers 8: comparison of experimental results for three impellers with shroud redesigned by rapid approximate method
- Report presenting a comparison of three centrifugal impellers with parabolic, circular, and skewed-parabolic blading that were modified using a recently developed design procedure to reduce velocity gradients along the hub from inlet to outlet. All of the original dimensions except for the shroud contours were retained. Results regarding a comparison of the original and modified parabolic-bladed, circular-bladed, and skewed-parabolic bladed impeller are provided.
- Determination of Burnout Limits of Polyphenyl Coolants: Research and Development Report
- Abstract: An experimental investigation was conducted to establish the burnout limit of liquid diphenyl for various flow conditions.
- The Determination of Fission Product Gamma Doses
- In this paper arbitrary limits of the general fission source gamma problem are set. Then, by assuming cooling of at least one day, it is shown that only twelve different fission product gamma sources need ever be considered.
- Diamond drilling in the Silver Reef (Harrisburg) district and adjacent areas, Washington County, Utah
- A report discussing a diamond drilling project in the Silver Reef District and adjacent areas, with the propose to obtain geologic information as well as to further explore the Chinle formation for new ore bodies.
- Differential equations of motion for combined flapwise bending, chordwise bending, and torsion of twisted nonuniform rotor blades
- The differential equations of motion for the lateral and torsional deformations of twisted rotating beams are developed for application to helicopter rotor and propeller blades. No assumption is made regarding the coincidence of the neutral, elastic, and mass axes, and the generality is such that previous theories involving various simplifications are contained as subcases to the theory presented in this paper. Special attention is given the terms which are not included in previous theories. These terms are largely coupling-type terms associated with the centrifugal forces. Methods of solution of the equations of motion are indicated by selected examples.
- Distribution and Thickness of Salt in the Paradox Basin of Southwestern Colorado and Southeastern Utah, A Preliminary Report
- The following report covers investigation work done on the distribution of thick deposits of salt that had occurred in the Paradox member of the Hermosa formation of Pennsylvanian age in an area nearly 12,000 square miles of southwestern Colorado and southeastern Utah.
- Distribution and thickness of salt in the Paradox basin of southwestern Colorado and southeastern Utah: a preliminary report
- A report regarding the distribution and thickness of salt in the paradox basin of southeastern colorado and southeastern Utah. This report concerns work done on behalf of the Division of research of the U.S. Atomic Energy Commission.
- Ditching investigations of dynamic models and effects of design parameters on ditching characteristics
- From Summary: "Data from ditching investigations conducted at the Langley Aeronautical Laboratory with dynamic scale models of various airplanes are presented in the form of tables. The effects of design parameters on the ditching characteristics of airplanes, based on scale-model investigations and on reports of full-scale ditchings, are discussed. Various ditching aids are also discussed as a means of improving ditching behavior."
- Doloresite, A New Vanadium Oxide Mineral from the Colorado Plateau
- The following report studies the occurrence of the vanadium oxide mineral, doloresite, that has been identified in 11 mines on the Colorado Plateau.
- Dynamic Stability Investigation of Two Right Circular Cylinders in Axial Free Flight at Mach Numbers From 0.4 to 1.7 Fineness-Ratio- 2.56 Cylinder and Fineness-Ratio-4.0 Cylinder With Flared Afterbody
- Memorandum presenting two right circular cylinders tested in axial free flight over a Mach number range of 0.4 to 1.7 by using the rocket-boosted-model technique. Results regarding time history, basic data cross plots, center of pressure, and drag are provided.
- Effect of fiber orientation on ball failures under rolling-contact conditions
- The rolling-contact fatigue spin rig was used to test balls of a bearing steel at maximum Hertz stresses of 600,000 to 750,000 psi. The effect of fiber orientation was observed with the ball track restricted to passing directly over the poles, coincident with the equator, or randomly around the ball. The polar areas were found to be weaker in fatigue than the nonpolar areas. This resulted in a much greater portion of the failures occurring in the polar areas than would be expected from a homogeneous material. The early failures are discussed.
- Effect of Frequency and Temperature on Fatigue of Metals
- Note presenting a qualitative approach to the problem of the effect of frequency and temperature on fatigue, as the theoretical and experimental results do not always seem to match. The fatigue problem is examined from the viewpoint of a two-component system.
- Effect of HRT Core Sample Holder Upon Core Flow Pattern and Pressure Drop
- The measured pressure drop across the reactor core, with the sample holder in place, is 6.9 psi, more than twice the estimated value. Better estimates, based on more rigorous mathematical analysis, should be possible for future problems of this type. The 2% density difference which produced the relatively high velocity of approximately 1 fps, in this experiment, will result from a temperature difference of about 8 C. It is concluded that the bulk fluid temperature near the sample holder will be less than 8 C above the average temperature at the same elevation in the core.
- Effect of Pressure Differentials on Deflection of the Outer Fuel Plates of Brazed APPR Fuel Elements
- One of the considerations in designing a flat plate fuel element is the resistance of the fuel plates, especially the outer plates in the fuel plate array, to deflection and permanent deformation as a result of pressure differentials. An investigation was recently initiated wit the objective of obtaining preliminary information on the APPR-type fuel element to determine the effect of pressure differentials on the outer plates in the fuel assembly. The APPR-1 fuel element consists of 18 flat composite stainless steel fuel plates, joined to grooved 50 mil thick type 304L stainless steel side plates by brazing with Coast Metals N. P. alloy.
- Effectiveness at transonic speeds of flap-type ailerons for several spanwise locations on a 4-percent-thick sweptback-wing-fuselage model with and without tails
- Report presenting a transonic investigation in the 16-foot transonic tunnel to determine the effects of spanwise location of a flap-type aileron on the lateral characteristics of a 4-percent-thick sweptback-wing-fuselage model. Results regarding the effect of aileron spanwise position on roll and lift effectiveness, tail effects, and effect of spanwise aileron position on complete model rolling-moment characteristics are provided.
- Effects of conical camber on the lift, drag, and pitching-moment characteristics of a triangular wing of aspect ratio 3.0
- Report presenting the results of an investigation to determine the effects of conical camber on the lift, drag, and pitching-moment characteristics of a wing-body combination with a triangular wing of aspect ratio 3.0. At subsonic speeds, the use of camber was found to result in substantial reductions in drag coefficients at lift coefficients above 0.15.
- Effects of Radon in Drill Holes on Gamma-Ray Logs
- A report about drill holes in uranium in the Todilto limestone of Late Jurassic age near New Mexico which does not yield duplicate gamma-ray logs when probed at different times.
- Electrolytic Reduction of Thorium Oxide
- From abstract: "Thorium metal has been produced by electrolytic reduction of thorium oxide. Reduction was accomplished in both a KF-ThF4 melt and a NaCl-KCl-ThCl4 melt. A flowsheet for the complete process using the fused fluoride system is proposed."
- Equation of State and Heat Content of Uranium
- Report issued by the APDA regarting studies conducted on the state of uranium at different temperature and pressure. Calculations are presented for the differing pressures of uranium; it includes tables.
- Examination of Donut on Rupture Slug No. 14
- Pursuant to Dr. Kingdon's request for specific information concerning the donut pictured on pages 26-29 of WAPD-64, a close examination of this defect on Failure No. 14 was made. The slug was examined through 10 inches of Pb-glass and photographs were made. A clay impression of the surface area containing the donut was obtained, and using this impression, an Armstrong's Adhesive replica of this can wall surface area was cast.
- Experimental Investigation of a 0.4 Hub-Tip Diameter Ratio Axial-Flow Compressor Inlet Stage at Transonic Inlet Relative Mach Numbers 4: Performance of Tapered-Tip Rotor Configuration with Reset Blade Angles
- Memorandum describing the blades of the tapered-tip 0.4 hub-tip diameter ratio transonic rotor, which were reset 7.5 degrees in the rotor disk and twisted from 0 degrees at the mean-radius section to 4.5 degrees at the tip to increase the specific weight flow approximately 10 percent to 36.3 pounds per second per square foot of frontal area. Results regarding the rotor overall performance, rotor flow parameters, comparison of blade-element performance and design rules, and minimum-loss and choking incidence-angle analysis at rotor hub section are provided.
- Experimental Investigation of a Method of Wave-Drag Reduction for Combinations Employing Quasicylindrical Bodies and Swept Wings at Supersonic Speeds
- "Axisymmetric and nonaxisymmetric body distortions designed by the method of NACA TN 3722 were tested to determine the amount of wave-drag reduction obtainable when applied to swept-wing-body combinations over a Mach number range of 1.39 to 1.97. Two wings of aspect ratios 1.33 and 2.67 were tested on different bodies. Both the axisymmetric and nonaxisymmetric distortions produced drag reductions" (p. 1).
- Experimental investigation of dynamic relations in a 48-inch ram-jet engine
- Engine dynamics were investigated for supercritical operation of the ram jet at Mach 2.75 over a range of simulated altitudes from 68,000 to 82,000 feet. Indicial-and frequency-response tests were conducted with fuel flow as the input variable. For a wide range of operating points, the response of static or total pressure to fuel flow consisted of a dead time followed by a response form that generally approximated a linear, first-order, lead-lag. The dead time varied significantly only with distance from the combustion zone. The rise ratio and the time constant of the lead-lag function were nearly independent of the pressure sensed.
- Experimental investigation of ejector-nozzle metal temperatures
- Metal temperatures were obtained on a full-scale ejector nozzle installed on an afterburner operating at exhaust-gas temperatures up to 3450 degrees R. A favorable afterburner-outlet temperature profile helped keep the primary-jet nozzle components cool. The ejector shroud temperatures were much more sensitive to secondary airflow than were temperatures on the primary-jet nozzle.
- Experimental study of the effects of scale on the absolute values of zero-lift drag of aircraft configurations at transonic speeds
- Report presenting an investigation at a range of Mach numbers from 0.7 to 1.4 to determine the effect of scale on the zero-lift drag of a fin-stabilized body of revolution and a fighter-type airplane configuration. Results obtained at low values of Reynolds number were compared with larger scale data obtained on geometrically similar models in free flight. Results regarding fin-stabilized body and airplane model are provided.
- Exploratory Investigation of the Effect of Wing Slots and Leading-Edge Slats on the Longitudinal Stability Characteristics of a 45 Degree Sweptback Wing-Fuselage Configuration
- Report presenting an exploratory investigation to determine the effects of wing slots on the longitudinal stability characteristics of a 45 degree sweptback wing-fuselage combination. Results regarding pitching-moment characteristics and lift and drag characteristics are provided.
- Extraction of Metal Ions with Di-2-Ethylhexyl Phosphoric Acid
- Blake and his co-workers have shown that uranium and other elements can be extracted from acid solutions by various type of organo-phosphorous compounds. Early investigations in the laboratory have demonstrated the applicability of tri-n-alkyl phosphine oxides to the extraction of metal ions from acidic solutions for analytical purposes. This paper is concerned with a similar qualitative investigation of the extraction of metal ions with a di-alkyl phosphoric acid, di-2-ethylhexyl phosphoric acid (D2EPHA).
- Free-Flight Experience of the Lateral Stability Characteristics at Low Lift of a 45 Degree Swept-Wing Rocket-Propelled Model Equipped With a Nonlinear Yaw-Rate Damper System at Mach Numbers From 0.76 to 1.73
- Report discussing a low-lift lateral stability investigation with a rocket-propelled model of a 45 degree swept-wing-airplane configuration equipped with an auxiliary yaw-rate damper system at a range of Mach numbers. Results indicated that the system was nonlinear due to a large dead spot in the system. The primary effect of the system was to increase the damping of lateral oscillations.
- Free-jet tests of a 1.1-inch-diameter supersonic ram-jet engine
- Results are presented of free-jet tests of a 1.1-inch-diameter hydrogen-burning ram-jet engine over a Mach number range from 1.42 to 2.28 and a Reynolds number range from 6.01 times 10 to the 6th power to 15.78 times 10 to the 6th power. Tests demonstrated the reliability and wide operating range of the engine and showed its suitability for installation on wind-tunnel models of airplane and missile configurations. A comparison of engine operation with combustion-chamber lengths of 3.33 and 1.51 engine diameters was made at a Mach number of 2.06. A maximum test thrust coefficient of 0.905 was obtained at fuel-air ratio of 0.034 and a Mach number of 2.06 for the engine with the 3.33-diameter combustion chamber.
- Frequency Response of Weighted Voids VS. Power
- A method for calculating the frequency response of weighted voids (proportional to reactivity of steam voids) as a function of reactor power is presented.
- Fuel Costs in Batch- and Continually-Processed Homogeneous Reactors
- The fuel requirement of a heavy-water moderated, homogenous, power reactor were estimated for a variety of initial loadings, for both bath and continuous methods of fuel removal. This study considered a 12-ft spherical reactor, temperature 250 C, 500 Mw thermal power, 125 Mw electrical power capability, 0.8 load factor, and 4%/year inventory charges for U and D2O. The fuel shipping-and-processing charges were assumed to be $1/gm of fissionable fuel for the "batch" processed reactors, and $0.37/gm for the "continuous" processed reactors, Under these conditions, the minimum fuel costs associated with a 10-year 'batch" operating period were about 1.8 or 3.1 mills/kw-hr, if highly enriched U cost $15/gm or $20/gm, respectively. the analogous costs for the "continuous" processed reactor were about 1.6 and 2.6 mills/kw-hr, respectively.
- A General System for Calculating Burning Rates of Particles and Drops and Comparison of Calculated Rates for Carbon, Boron, Magnesium, and Isooctane
- Report presenting a system of general equations for computing the burning rates of small particles burning as diffusion flames. Two types of solutions are carried out: a complex numerical integration and a less complicated and rigorous analytical solution involving stepwise iteration across the temperature profile.
- Ground Simulator Studies of the Effects of Valve Friction, Stick Friction, Flexibility, and Backwash on Power Control System Quality
- Report presents results of tests made on a power control system by means of a ground simulator to determine the effects of various combinations of valve friction and stick friction on the ability of the pilot to control the system. Various friction conditions were simulated with a rigid control system, a flexible system, and a rigid system having some backlash. For the tests, the period and damping of the simulated airplane were held constant.
- Hazards Summary Report for the Reflector-Control Critical-Assembly Experiments
- This report analyzes the stability and feasibility of a reflector-control system for a boiling heterogeneous reactor.