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P-P Elastic and Charge-Exchange Scattering at about 120 Mev

Description: Observation of antiprotons in a propane or hydrogen bubble chamber offers the possiblity of studying several phenomena for which counter or photographic emulsion techniques are less suitable. Because there is a high ratio of pions, muons, and electrons to antiprotons in the available momentum-analyzed beams, these beams cannot be used in the bubble chamber without an initial purification, which increases the ratio of antiprotons to other particles. Such a purification has been achieved by utili… more
Date: March 28, 1958
Creator: Agnew, Lewis E., Jr.; Elioff, Tom; Fowler, William B.; Gilly, Louis; Lander, Richard L.; Oswald, Larry et al.
Partner: UNT Libraries Government Documents Department
open access

Thorex Pilot Plant: System for Concentrating Second Uranium

Description: A system for concentrating uranyl nitrate solutions was designed and installed in the Thorex Pilot Plant. A total of 16,060 g of uranium was concentrated in the system in 68 batch runs. A total of 14,400 g total uranium (14.180 g U/sup 233/) was recovered as product suitable for shipment. Uranium loss to the evaporator condensate was 0.03% of ihe total uranium processed. The material balance across the system was 98.4%. The average concentration of uranium in the evaporator feed solution was 29… more
Date: January 28, 1957
Creator: Albrecht, W. L.
Partner: UNT Libraries Government Documents Department
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Thorex Pilot Plant ; System for Concentrating Second Uranium Cycle Product

Description: A system for concentrating uranyl nitrate solutions was designed and installed in the Thorex Pilot Plant. A total of 16,060 g of uranium was concentrated in the system in 68 batch runs. A total of 14,400 g total uranium (14.180 g U/sup 233/) was recovered as product suitable for shipment. Uranium loss to the evaporator condensate was 0.03% of the total uranium processed. The material balance across the system was 98.4%. The average concentration of uranium in the evaporator feed solution was 29… more
Date: January 28, 1957
Creator: Albrecht, W. L.
Partner: UNT Libraries Government Documents Department
open access

Intermediate Heat Exchanger Preliminary Design. Vol. 1, IHX Preliminary Design

Description: Preface: The intermediate heat exchanger is designed for operation in a nuclear power plant using liquid sodium as the primary and secondary coolant. Since the primary fluid coming from the reactor is radioactive, the purpose of the IHX is to transfer heat to a nonradioactive fluid which then goes to a steam generator. Because of this activity the until will be enclosed in a concrete pit and will not be accessible during periods of operation. Immediately after shut down it will be necessary … more
Date: February 28, 1959
Creator: Alco Products (Firm)
Partner: UNT Libraries Government Documents Department
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A study of the motion and aerodynamic heating of ballistic missiles entering the earth's atmosphere at high supersonic speeds

Description: From Summary: "A simplified analysis of the velocity and deceleration history of ballistic missiles entering the earth's atmosphere at high supersonic speeds is presented. The results of this motion analysis are employed to indicate means available to the designer for minimizing aerodynamic heating. The heating problem considered involves not only the total heat transferred to a missile by convection, but also the maximum average and local time rates of convective heat transfer."
Date: April 28, 1953
Creator: Allen, H. Julian & Eggers, A. J., Jr.
Partner: UNT Libraries Government Documents Department
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Performance of a blunt-lip side inlet with ramp bleed, bypass, and a long constant-area duct ahead of the engine : Mach number 0.66 and 1.5 to 2.1

Description: Unsteady shock-induced separation of the ramp boundary layer was reduced and stabilized more effectively by external perforations than by external or internal slots. At Mach 2.0 peak total-pressure recovery was increased from 0.802 to 0.89 and stable mass-flow range was increased 185 percent over that for the solid ramp. Peak pressure recovery occurred just before instability. The 7 and one-third-diameter duct ahead of the engine reduced large total-pressure distortions but was not as successfu… more
Date: December 28, 1956
Creator: Allen, John L.
Partner: UNT Libraries Government Documents Department
open access

Performance of a Blunt-lip Side Inlet With Ramp Bleed, Bypass, and a Long Constant-area Duct Ahead of the Engine- Mach Numbers 0.66 and 1.5 to 2.1

Description: Report presenting the performance of a side inlet with a fixed 12 degree two-dimensional compression surface for a range of Mach numbers, angles of attack, and yaw. The effects of several methods of compression-surface boundary-layer removal were investigated as well as a solid ramp.
Date: December 28, 1956
Creator: Allen, John L.
Partner: UNT Libraries Government Documents Department
open access

Measurement and Calculation of Blade Torsional Deflection of Three Supersonic-Type Propellers

Description: Report presenting an investigation to determine the blade torsional deflection of three supersonic-type propellers at various operating conditions. Blade-torsional deflection was found to produce appreciable results that can be predicted by theory with good accuracy. Results regarding the efficiency, thrust coefficient, and power coefficient are provided.
Date: May 28, 1954
Creator: Allis, Arthur E. & Foss, Willard E., Jr.
Partner: UNT Libraries Government Documents Department
open access

Free-flight Investigation at Transonic Speeds of the Stability Characteristics of a Tailless Missile Configuration Having a 45 Deg Sweptback Wing of Aspect Ratio 4

Description: Free flight test of tailless missile configuration with 45-deg sweptback wing of aspect ratio 4 - stability at transonic speeds. The longitudinal flexible-wing results indicated a gradual transonic trim change a lift-curve slope comparable with that for the same configuration with a wing of aspect ratio 5.5. Results regarding trim characteristics, lift and longitudinal stability, and side-force and lateral stability are provided.
Date: August 28, 1956
Creator: Arbic, Richard G.
Partner: UNT Libraries Government Documents Department
open access

Free-Flight Investigation at Transonic Speeds of the Stability Characteristics of a Tailless Missile Configuration Having a 45 Degree Sweptback Wing of Aspect Ratio 4

Description: Memorandum presenting a flight test of a long-range missile configuration with a 45 degree sweptback wing of aspect ratio 4 conducted at a range of Mach and Reynolds numbers. The longitudinal flexible-wing results indicated a gradual transonic trim change and a lift-curve slope comparable with that for the same configuration with a wing of aspect ratio 5.5.
Date: August 28, 1956
Creator: Arbic, Richard G.
Partner: UNT Libraries Government Documents Department
open access

PROBLEMS IN ACCOUNTABILITY MEASUREMENTS ASSOCIATED WITH THE INTERIM CHEMICAL PROCESSING PROGRAM

Description: Available knowledge of precision limits in S.S. accountability measurements and/or calculations by reactor and chemical processing groups is surveyed and summarized. Experienee in comparisons of reactor (production and research) calculations vs. chemical plant accountability measurements is also reported. A general tentative conclusion is that available precisions ( plus or minus 0.54 to plus or minus 0.78%) in chemical plant measurements (bulk and analytical) for fissionable material accountab… more
Date: May 28, 1959
Creator: Arnold, E D & Gresky, A T
Partner: UNT Libraries Government Documents Department
open access

Fission Product Activities in Irradiated Natural Uranium, Enriched Uranium, and Thorium

Description: Calculated data and graphs describing the effects of batch thermal-neutron irradiations on the buildup of fission products in natural uranium, enriched uranium, and thorium are presented together with empirical equations and plots correlating total fission product activities and/or decontamination factors. Fluxes of 1012-1015 are considered.
Date: March 28, 1956
Creator: Arnold, E. D.
Partner: UNT Libraries Government Documents Department
open access

Problems in Accountability Measurements Associated with the Interim Chemical Processing Program

Description: Available knowledge of precision limits in S.S. accountability measurements and/or calculations by reactor and chemical processing groups is surveyed and summarizes. Experience in comparisons of reactor (production and research) calculations versus chemical plant accountability measurements is also reported. A general tentative conclusion is that available precisions (+/- 0.54 to +/- 0.78% ) in chemical plant measurements is also reported. A general tentative conclusion is that available precis… more
Date: May 28, 1959
Creator: Arnold, E. D. & Gresky, A. T.
Partner: UNT Libraries Government Documents Department
open access

K [infinity] in Uranium - Water Lattices

Description: This report follows experiments on K[infinity], measuring the element for several red sizes, enrichments, and water-to-uranium volume ratios-(1, 2), by making use of the relation k[infinity] = 0M-[2]B-[2] (M-2 = migration area, B = buckling). The purpose of this report is to compare the experimental data for k[infinity] with values calculated from the four-factor formula k[infinity] = [eta][epsilon]pf.
Date: July 28, 1955
Creator: Auerback, T.
Partner: UNT Libraries Government Documents Department
open access

Longitudinal Stability and Control Characteristics as Determined by the Rocket-Model Technique for an Inline, Cruciform, Canard Missile Configuration With a Low-Aspect-Ratio Wing Having Trailing-Edge Flap Controls for a Mach Number Range of 0.7 to 1.

Description: Report presenting tests of two models of an inline, cruciform, canard missile configuration with a low-aspect-ratio wing equipped with flap-type controls to determine the missile's longitudinal aerodynamic characteristics. Stability derivatives and control and drag characteristics are presented for a range of Mach numbers.
Date: September 28, 1955
Creator: Baber, Hal T., Jr. & Moul, Martin T.
Partner: UNT Libraries Government Documents Department
open access

Longitudinal Stability and Control Characteristics as Determined by the Rocket-Model Technique for an Inline, Cruciform, Canard Missile Configuration With a Low-Aspect-Ratio Wing Having Trailing-Edge Flap Controls for a Mach Number Range of 0.7 to 1.8

Description: Report presenting testing of two full-scale models of an inline, cruciform, canard missile configuration with a low-aspect-ratio wing equipped with flap-type controls to determine the missile's longitudinal aerodynamic characteristics. Stability derivatives and control and drag characteristics are provided.
Date: September 28, 1955
Creator: Baber, Hal T., Jr. & Moul, Martin T.
Partner: UNT Libraries Government Documents Department
open access

Calibration of a Peak Current Gage Developed at Sandia Corporation

Description: Abstract: Methods are presented for calibrating a peak current gage which was developed at Sandia in the spring of 1953.
Date: December 28, 1953
Creator: Baker, G. E.; Looney, T. C.; Pafford, W. B. & Reis, George E.
Partner: UNT Libraries Government Documents Department
open access

Chemical and physical factors affecting combustion in fuel-nitric acid systems

Description: Report presenting characteristic exhaust-velocity measurements made of the JP-4 fuel-red fuming nitric acid propellant combination in 40-pound-thrust rocket engines with various combustion-chamber lengths and diameters. The results are compared to those from previous studies and discussed in terms of a vaporization model of combustion. Results regarding the effect of UDMH, effect of water on performance of hydrocarbon fuels, effect of water on performance of hydrazine fuel, and some of the chem… more
Date: July 28, 1958
Creator: Baker, Louis, Jr.
Partner: UNT Libraries Government Documents Department
open access

Some Measurements of the Buffet Region of a Swept-Wing Research Airplane During Flight to Supersonic Mach Numbers

Description: Report presenting measurements of the intensity of buffeting experienced by the Douglas D-558-II research airplane at a range of Mach numbers. Buffeting was encountered at both subsonic and supersonic Mach numbers and the intensity of the buffeting varied with Mach number and airplane normal-force coefficient.
Date: May 28, 1953
Creator: Baker, Thomas F.
Partner: UNT Libraries Government Documents Department
open access

Flight Measurements at Transonic Speeds of the Buffeting Characteristics of the XF-92A Delta-Wing Research Airplane

Description: Report presenting testing on a 60 degree delta-wing XF-92A airplane at a variety of Mach numbers to obtain measurements regarding buffet-induced fluctuations in normal acceleration and of fluctuations in structural shear load of the left wing. The altitudes tested ranged from 25,000 to 38,000 feet. Results regarding the buffet boundary, wing flow conditions, buffet frequencies, buffet intensities, and a comparison to buffeting of other airplanes are provided.
Date: April 28, 1955
Creator: Baker, Thomas F. & Johnson, Wallace E.
Partner: UNT Libraries Government Documents Department
open access

Application of wing-body theory to drag reduction at low supersonic speeds

Description: Report presenting a method for extending to higher Mach numbers the region of low drag attainable for wing-body combinations by the use of the transonic area rule. To a good approximation, the drag depends only on the longitudinal distributions of area and moments of area about the vertical plane of symmetry parallel to the free-stream direction. The experimental results confirm the theory in that the zero-lift wave drag of a wing-body configuration over a range of low supersonic Mach numbers.
Date: January 28, 1955
Creator: Baldwin, Barrett S., Jr. & Dickey, Robert R.
Partner: UNT Libraries Government Documents Department
open access

A Further Evaluation of the Calder Hall Type of Nuclear Power Plant

Description: Abstract: This report presents the results of plant optimization studies and cost estimates of the reference design for a natural uranium, graphite moderated, gas-cooled reactor and power plant which was described in NAA-SR-1833.
Date: June 28, 1957
Creator: Banks, William F.
Partner: UNT Libraries Government Documents Department
open access

Boundary-Layer-Transition Measurements in Full-Scale Flight

Description: Chemical sublimation has been employed for boundary-layer-flow visualization on the wings of a supersonic fighter airplane in level flight at speeds near a Mach number of 2.0. The tests have shown that laminar flow can be obtained over extensive areas of the wing with practical wing-surface conditions. In addition to the flow visualization tests, a method of continuously monitoring the conditions of the boundary layer has been applied to flight testing, using heated temperature resistance gages… more
Date: July 28, 1958
Creator: Banner, Richard D.; McTigue, John G. & Petty, Gilbert, Jr.
Partner: UNT Libraries Government Documents Department
open access

Boundary-Layer-Transition Measurements in Full-Scale Flight

Description: Report presenting tests of the extent of laminar flow that can be obtained with practical wing-surface conditions. Chemical sublimation was used for boundary-layer-flow visualization on the wings of a supersonic fighter airplane in level flight. A method of continuous monitoring using heat temperature resistance gauges was also used on one wing.
Date: July 28, 1958
Creator: Banner, Richard D.; McTigue, John G. & Petty, Gilbert, Jr.
Partner: UNT Libraries Government Documents Department
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