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Aerodynamic characteristics at Mach number 4.04 of a rectangular wing of aspect ratio 1.33 having a 6-percent-thick circular-arc profile and a 30-percent-chord full-span trailing-edge flap

Description: From Introduction: "The present report gives results at a Mach number of 4.04 of the part of the program concerned with flap controls at Mach numbers from 1.62 to 6.9."
Date: May 29, 1953
Creator: Dunning, Robert W. & Ulmann, Edward F.
Partner: UNT Libraries Government Documents Department
open access

Altitude investigation of XJ34-WE-32 engine performance without electronic control

Description: From Introduction: "As a part of the comprehensive investigation of the XJ34-WE-32 engine conducted in the NACA Lewis altitude wind tunnel, the over-all-performance was determined over a range of altitudes and flight Mach numbers. Other phases of the investigation are reported in reference 1. The results are given in tables and also in graphical form to show the trends of engine performance associated with changes of altitude, flight Mach number, and exhaust-nozzle area."
Date: May 29, 1953
Creator: Bloomer, Harry E.; Walker, William J. & Pantages, George L.
Partner: UNT Libraries Government Documents Department
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Altitude Performance Investigation of Two Single-Annular Type Combustors and the Prototype J40-WE-8 Turbojet Engine Combustor With Various Combustor-Inlet Air Pressure Profiles

Description: Report presenting data obtained three single annular-type combustors with different combustor inlet-air pressure profiles over a range of engine speeds. Results regarding effect of changing combustor inlet-air pressure profile and hole geometry on combustor performance, performance of the prototype J40-WE-8 turbojet engine combustor, correlation of combustion efficiency with engine fuel-air ratio and combustion parameter, and comparison of several combustors from different turbojet engines are … more
Date: May 29, 1953
Creator: Sobolewski, Adam E.; Miller, Robert R. & McAulay, John E.
Partner: UNT Libraries Government Documents Department
open access

Angular Distribution of Fragments from Neutron-Induced Fission

Description: The angular distribution of fission fragments from the neutron-induced fission of several isotopes has been studied. Distributions were observed for thermal neutrons on U233 and U235, Lady Godiva leakage neutrons on U235 and U238, and 14 Mev neutrons on U233, U235, U238, Th232, and Np237. No anisotropy was observed for thermal neutron fission, whereas for Lady Godiva neutrons and 14 Mev neutrons the probability of fission along the axis of the neutron beam was determined to be higher than for f… more
Date: May 7, 1953
Creator: Brolley, John Edward, 1919- & Dickinson, W. C.
Partner: UNT Libraries Government Documents Department
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The attenuation characteristics of four specially designed mufflers tested on a practical engine setup

Description: Attenuation characteristics of four different resonator mufflers were determined in both cold tests and engine field tests and compared with the theoretical calculations. These mufflers were specifically designed for a helicopter. Engine-exhaust sound pressures, temperatures, and noise levels from the helicopter were measured. The experimental muffler cold tests indicated close a agreement with theory, whereas the engine tests indicated some discrepancies. Test results show the usefulness of th… more
Date: May 1953
Creator: Stokes, George M. & Davis, Don D., Jr.
Partner: UNT Libraries Government Documents Department
open access

Beta In Line Monitor for RCU Stream

Description: Interest has been expressed in continuously monitoring the beta activity of the uranyl nitrate solution pumped to the RCU receiver tank, to facilitate operation at higher flow rates and with younger feeds. A beta scintillation detector has been developed which should make this feasible, and it is proposed that it be tested on stream for this use.
Date: May 1953
Creator: Leboeuf, M. B. & Connally, R. E.
Partner: UNT Libraries Government Documents Department
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Calculated spanwise lift distributions, influence functions, and influence coefficients for unswept wings in subsonic flow

Description: Spanwise lift distributions have been calculated for nineteen unswept wings with various aspect ratios and taper ratios and with a variety of angle-of-attack or twist distributions, including flap and aileron deflections, by means of the Weissinger method with eight control points on the semispan. Also calculated were aerodynamic influence coefficients which pertain to a certain definite set of stations along the span, and several methods are presented for calculating aerodynamic influence func… more
Date: May 5, 1953
Creator: Diederich, Franklin W. & Zlotnick, Martin
Partner: UNT Libraries Government Documents Department
open access

Calculation of Stagewise Contacting Systems

Description: From abstract: General expressions relating product stream compositions to the operating conditions of countercurrent stagewise extraction columns are derived by an inductive method, and the conversion of the general equations to ones involving the particular case of constant extraction factor is demonstrated. For comparison, the derivation of simple column equations by the use of finite difference equations is included.
Date: May 22, 1953
Creator: Bloom, J. L. & Auer, P. L.
Partner: UNT Libraries Government Documents Department
open access

Chemical Engineering Division Summary Report : January, February, And March 1953

Description: Dissolution of the large number of samples obtained from the natural uranium blanket of the Experimental Breeder Reactor after approximately 485,000 kw.-hr. of operation has been completed, and analysis of these samples for uranium consumed and plutonium formed is well along. An attempt is being made to distinguish quantitatively between uranium-238 and uranium-235 fission in the blanket area by determining the ratio of ruthenium-106 to cesium-137 in the fission products.
Date: May 12, 1953
Creator: Lawroski, Stephen & Stevenson, C. E.
Partner: UNT Libraries Government Documents Department
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Combined-Stress Fatigue Strength of 76S-T61 Aluminum Alloy With Superimposed Mean Stresses and Corrections for Yielding

Description: Note presenting fatigue data for 76S-T61 aluminum alloy for several combinations of bending and torsion with both alternating and mean stresses. The literature on the effect of combined stress and of mean stress in fatigue is reviewed and the results of the present series are compared with those of various theories. Results regarding fatigue data, fatigue fractures, and static tests are provided.
Date: May 1953
Creator: Findley, William N.
Partner: UNT Libraries Government Documents Department
open access

Combustion instability in an acid-heptane rocket with a pressurized-gas propellant pumping system

Description: Report presenting results of experimental measurements of low-frequency combustion instability of a 300-pound-thrust acid-heptane rocket engine as compared with the trends predicted by an analysis of combustion instability in a rocket engine. Results regarding the chugging frequency, combustion time delay, effect of rocket combustion-chamber characteristic length, effect of throttling, effect of injection velocity, effect of oxidant-fuel ratio, variation of chugging frequency with amplitude of … more
Date: May 1953
Creator: Tischler, Adelbert O. & Bellman, Donald R.
Partner: UNT Libraries Government Documents Department
open access

Comparison of the aerodynamic characteristics at transonic speeds of a plane wing and a cambered and twisted wing, both having 45 degrees of sweepback and an aspect ratio of 6

Description: Report presenting a transonic investigation made by the free-fall technique of a plane wing and a cambered and twisted wing, each with an aspect ratio 6, taper ratio of 0.5, and a sweepback of 45 degrees. Measurements were made of the loads on the exposed wings, pressures on the fuselage in the vicinity of the wing, and acceleration and angle of attack of the complete model.
Date: May 5, 1953
Creator: Holdaway, George H.
Partner: UNT Libraries Government Documents Department
open access

The Creep of Single Crystals of Aluminum

Description: The creep of single crystals of high-purity aluminum was investigated in the range of temperatures from room temperature to 400 F and at resolved-shear-stress levels of 200, 300, and 400 psi. The tests were designed in an attempt to produce data regarding the relation between the rate of strain and the mechanism of deformation. The creep data are analyzed in terms of shear strain rate and the results are discussed with regard to existing creep theories.
Date: May 1953
Creator: Johnson, R. D.; Shober, F. R. & Schwope, A. D.
Partner: UNT Libraries Government Documents Department
open access

Creep Strength of Uranium Alloys at 1500 and 1800 F

Description: Abstract:"The creep resistance of various uranium binary alloys was investigated at 1500 and 1800 F in vacuum. Tests were made on alloys of uranium with beryllium, columbium, molybdenum, tantalum, titanium, and zirconium and on molybdenum-UO2 composites. Of the alloys examined, those of the uranium-molybdenum system exhibited the best creep resistance. At 1500 F, creep rates of about 0.005%/hr were produced in uranium-molybdenum alloys by a stress of 2500 psi and, at 1800 F, similar creep rates… more
Date: May 28, 1953
Creator: Saller, Henry A.; Stacy, J. T.; Eddy, N. S. & Klebanow, H. L.
Partner: UNT Libraries Government Documents Department
open access

Decontamination of Portable Instruments

Description: The decontamination of portable instruments by the Calibration Unit has presented a problem for some time. Most of the contamination is in the 100 to 500 c/m or 500 to 2000 d/m range. Higher levels of contamination can usually be reduced to these levels, but further cleaning proves quite difficult
Date: May 22, 1953
Creator: Unruh, C. M.
Partner: UNT Libraries Government Documents Department
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Deflection of Delta Wings Having a Carry-Through-Bay Chord Smaller than the Wing Root Chord

Description: Note presenting experimentally determined influence coefficients for the deflection of two solid delta wings - one wing of constant thickness and the other of constant thickness ratio - with a carry-through-bay chord smaller than the wing root chord. The experimental tip-load deflections of the constant-thickness wing exceed those computed by the present theory by approximately 15 to 20 percent at the tip.
Date: May 1953
Creator: Peters, Roger W. & Stein, Manuel
Partner: UNT Libraries Government Documents Department
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DENSITIES AND BOILING POINTS OF URANYL NITRATE-NITRIC ACID SOLUTIONS

Description: The intercycle evaporators in the Chemical Processing Plant are controlled by density-measuring instruments. Because of difficulties in controlling these evaporators in a satisfactory manner, a series of investigations was begun to measure the boiling points at the elevation of the CPP, and densities near boiling temperatures of a number of solutions in the uranyl nitrate-nitric acid-water system. From these data it was hoped to evaluate temperature sensitve devices as controllers for the evapo… more
Date: May 6, 1953
Creator: Perkins, R.H.
Partner: UNT Libraries Government Documents Department
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Development of a Process to Produce Zirconium Hanford Type Process Tubing by Roll Forming And Inert Arc Welding

Description: The development of methods which were successful in producing zirconium Hanford type process tubing by roll forming and inert are welding (He) flat strip to which appropriate rails had ben previously attached by resistance welding is described in this report. Grade 2 drip arc melted crystal bar material was used.
Date: May 1, 1953
Creator: Noland, R. A. & O'Keefe, G. B.
Partner: UNT Libraries Government Documents Department
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Drag and Longitudinal Trim at Low Lift of the North American YF-100A Airplane at Mach Numbers from 0.76 to 1.77 as Determined from the Flight Test of a 0.11-Scale Rocket Model

Description: Drag and longitudinal trim at low lift of the North American YF-100A airplane at Mach numbers from 0.76 to 1.77 as determined from the flight test of a 0.11-scale rocket model are presented herein. Also included are some longitudinal stability and some qualitative pitch-damping data.
Date: May 14, 1953
Creator: Blanchard, Willard S., Jr.
Partner: UNT Libraries Government Documents Department
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