[Aerosol Generator Design] : Letter Report (open access)

[Aerosol Generator Design] : Letter Report

The following report provides information on an aerosol generator fit to produce fine particles by a vaporization-condensation technique. Included is a diagram of the essential components of the generator.
Date: October 19, 1960
Creator: Rosinski, John & Stockham, John D.
System: The UNT Digital Library
Boiling of Freon-114 in a Three-Foot Straight Tube Evaporator (open access)

Boiling of Freon-114 in a Three-Foot Straight Tube Evaporator

Introduction: this report covers two series of tests run on a Freon evaporator containing a vertical copper tube having an outside diameter of 7/8 of an inch, heated externally for a length of 35 inches by steam condensing in a concentric jacket.
Date: October 19, 1961
Creator: Allen, Charles F.
System: The UNT Digital Library
Transonic Aerodynamic Characteristics of a 1/15-Scale Model of the Convair B-58 Airplane (open access)

Transonic Aerodynamic Characteristics of a 1/15-Scale Model of the Convair B-58 Airplane

Report presenting an investigation of a model of the Convair B-58 airplane weapons system in the transonic tunnel for a range of Mach and Reynolds numbers. Results regarding drag characteristics, lift-curve slope, and longitudinal stability parameter are provided.
Date: October 19, 1956
Creator: Swihart, John M.
System: The UNT Digital Library
An Experimental Investigation at Large Scale of Several Configurations of an NACA Submerged Air Intake (open access)

An Experimental Investigation at Large Scale of Several Configurations of an NACA Submerged Air Intake

"An investigation of an NACA submerged air intake was conducted on a full-scale model of a fighter-type airplane. This study was made to determine the large-scale aerodynamic characteristics of a submerged air intake proposed as the result of small-scale tests and to compare the pressure-recovery characteristics of the large- and small-scale installations. Additional tests were made to determine the effect on pressure recovery of a systematic variation of ramp divergence" (p. 1).
Date: October 19, 1948
Creator: Martin, Norman J. & Holzhauser, Curt A.
System: The UNT Digital Library
Investigation at a Mach Number of 1.93 to Determine Lift, Drag, Pitching-Moment, and Average Downwash Characteristics for Several Missile Configurations Having Rectangular Wings and Tails of Various Spans (open access)

Investigation at a Mach Number of 1.93 to Determine Lift, Drag, Pitching-Moment, and Average Downwash Characteristics for Several Missile Configurations Having Rectangular Wings and Tails of Various Spans

Memorandum presenting an investigation made at a Mach number of 1.93 to determine lift, drag, pitching-moment, and average downwash characteristics of several missile configurations. Five configurations with rectangular wings and tails of various spans were tested; each of the configurations had two locations of the wing relative to the tail.
Date: October 19, 1950
Creator: Grigsby, Carl E.
System: The UNT Digital Library
Summary report on the high-speed characteristics of six model wings having NACA 65(sub1)-series sections (open access)

Summary report on the high-speed characteristics of six model wings having NACA 65(sub1)-series sections

A summary of the results of wind-tunnel tests to determine the high-speed aerodynamic characteristics of six model wings having NACA 65sub1-series sections is presented in this report. The 8-percent-thick wings were superior to the 10-percent and 12-percent-thick wings from the standpoint of power economy during level flight for Mach numbers above 0.76. However, airplanes that are to fly at Mach numbers below 0.76 will gain aerodynamically if the percentage thickness of the wing and the aspect ratio are both increased. The lift-curve slopes for the 8-percent-thick wings at 0.85 Mach number were roughly twice their low-speed values.
Date: October 19, 1945
Creator: Hamilton, William T. & Nelson, Warren H.
System: The UNT Digital Library
Résumé of NACA Stability and Control Tests of the Bell P-63 Series Airplane (open access)

Résumé of NACA Stability and Control Tests of the Bell P-63 Series Airplane

Report on stability and control tests of the Bell P-63 series airplanes. Information about the spin characteristics, lateral control characteristics, longitudinal stability and control characteristics and directional stability and control characteristics is provided. A chronology of testing and detailed description of the airplane and its modifications are also provided.
Date: October 19, 1944
Creator: Johnson, Harold I.
System: The UNT Digital Library
Heat Transfer Characteristics of Graphite Plates with Hydrogen Coolant (open access)

Heat Transfer Characteristics of Graphite Plates with Hydrogen Coolant

"This note presents the results of a parametric study of heat-generating graphite plates with hydrogen coolant flowing through constant area passages. The heat generation within the graphite was assumed to have a distribution that allowed the centerline temperature of the plates to remain constant at 5000 F. The parametric variables were the mass flow rate per unit area, plate thickness, plate length, and passage hydraulic diameter. The machine calculations were coded by Ivan Cherry, T-1."
Date: October 19, 1955
Creator: Bussard, R. W. & Durham, F. P.
System: The UNT Digital Library
Accuracy of Volume Measurements in a Large Process Vessel (open access)

Accuracy of Volume Measurements in a Large Process Vessel

The Non-Production Fuel Reprocessing Program involves the chemical processing of valuable reactor fuels received from privately owned power reactors. It is necessary therefore, to accurately measure the fuel material received in order to insure proper payment to reactor operator and to provide the Atomic Energy Commission with appropriate accountability data. The volume measurement study described herein was conducted in order to determine the limits of accuracy that could be obtained in measuring relatively large volumes of solution under plant processing conditions.
Date: October 19, 1959
Creator: Pleasance, C. L.
System: The UNT Digital Library
Plutonium Oxalate Disk Filter and Filter Media Studies (open access)

Plutonium Oxalate Disk Filter and Filter Media Studies

Presently rotary drum filters are being used for plutonium oxalate slurry filtration in the 234-5 Building. Changing of the filter cloth used on a rotary drum is a time consuming operation which involves ever increasing radiation exposure to maintenance personnel. Consequently, studies were conducted in the 321 Building on a disk type filter which could be adapted for simple and quick ("one-nut") replacement of the filter medium.
Date: October 19, 1959
Creator: Rey, George
System: The UNT Digital Library
EOCR Control Rod and Driver Fuel Hydraulic Tests (open access)

EOCR Control Rod and Driver Fuel Hydraulic Tests

Report discussing the results of experiments on an EOCR prototype control rod, control rod drive, and driver fuel assembly that were extensively tested in 500 deg F Santowax and 132 deg F water. These tests not only established the operating characteristics of these assemblies but also revealed a number of deficiencies in the various components. It includes descriptions of the control rod, control rod drive, and driver fuel assembly together with descriptions of their method of operation.
Date: October 19, 1962
Creator: Harrison, L. J.
System: The UNT Digital Library
Some considerations of the influence of body cross-sectional shape on the lifting efficiency of wing-body combinations at supersonic speeds (open access)

Some considerations of the influence of body cross-sectional shape on the lifting efficiency of wing-body combinations at supersonic speeds

From Summary: "Linearized theory is used to estimate the order of magnitude of the beneficial effects that can be obtained by shaping the body of a wing-body configuration to generate lift indirectly at supersonic speeds. The analysis applies to a class of wing-body configurations which is believed to exhibit the essential features of this type of interference; the body is cylindrical upstream of a wing which has supersonic edges and the parts of the body above and below the wing are each semicircular and of different radii. Calculations are presented for a Mach number of the square root of 2 for a particular family of bodies and a sonic-edge delta wing."
Date: October 19, 1956
Creator: Klunker, E. B. & Harder, Keith C.
System: The UNT Digital Library
Effect of Camber on the Drag of a Body of Revolution (open access)

Effect of Camber on the Drag of a Body of Revolution

Memorandum presenting an investigation to determine the effect of camber on the drag of a body of revolution. The drag of a straight body of revolution was measured and compared with that of a body that differed only in that its center line was cambered in the form of a parabola. The addition of a small amount of camber was found to cause very little increase in the minimum foredrag of the model tested.
Date: October 19, 1956
Creator: Dickey, Robert R.
System: The UNT Digital Library
Effect of Blade-Section Camber on Aerodynamic Characteristics of Full-Scale Supersonic-Type Propellers at Mach Numbers to 1.04 (open access)

Effect of Blade-Section Camber on Aerodynamic Characteristics of Full-Scale Supersonic-Type Propellers at Mach Numbers to 1.04

Report presenting an investigation of the aerodynamic characteristics of two full-scale supersonic propellers with a 6000-horsepower propeller dynamometer. One propeller had symmetrical NACA 16-series airfoil sections and the other was similar except for a blade-section camber and a slight difference in pitch distribution.
Date: October 19, 1956
Creator: Maynard, Julian D.; Swihart, John M. & Norton, Harry T., Jr.
System: The UNT Digital Library
A Flight Investigation of the Ice-Prevention Requirements of the United States Naval K-Type Airship (open access)

A Flight Investigation of the Ice-Prevention Requirements of the United States Naval K-Type Airship

Report discussing a research program to investigate ice prevention and elimination on airships in order to develop suitable airship ice-prevention equipment. A Naval K-type airship was equipped with photographic and meteorological tools in order to record ice formation and the propellers were outfitted with electrically heated blade shoes. Testing discovered that an airship can be flown successfully in wet snow and freezing rain with only the propellers and induction systems protected from the weather.
Date: October 19, 1945
Creator: Hillendahl, Wesley H.
System: The UNT Digital Library
Effective Gust Structure at Low Altitudes as Determined From the Reactions of an Airplane (open access)

Effective Gust Structure at Low Altitudes as Determined From the Reactions of an Airplane

"Measurements of gust structure and gust intensity were made in the lower levels of the atmosphere (0 to 3,500 ft.). An Aeronca C-2 airplane was used as the measuring instrument, the gust structure being derived from the recorded motions of the airplane. Data were also obtained on wind velocities and temperatures as functions of altitude for use in attempting to correlate the gust-structure data with various meteorological quantities" (p. 263).
Date: October 19, 1939
Creator: Donely, Philip
System: The UNT Digital Library
Theoretical Investigation of a Proportional-Plus-Flicker Automatic Pilot (open access)

Theoretical Investigation of a Proportional-Plus-Flicker Automatic Pilot

"The proportional-plus-flicker automatic pilot operates by a nonlinear principle whereby a fast-acting flicker servomotor response is combined with a low-speed proportional servomotor response for the purpose of obtaining supersonic stability and control. Essentially, the autopilot maintains a zero reference about which the output is proportional to the input. However, a flicker response overrides this proportional response at a fixed angle of gimbal displacement on either side of the zero gyroscope reference" (p. 1).
Date: October 19, 1950
Creator: Seaberg, Ernest C.
System: The UNT Digital Library
Transonic Aerodynamic Characteristics of a 1/15-Scale Model of the Convair B-58 Airplane (open access)

Transonic Aerodynamic Characteristics of a 1/15-Scale Model of the Convair B-58 Airplane

Report presenting an investigation of a model of the Convair B-58 airplane weapons system, including under conditions of long-range subsonic cruise and a supersonic dash. Results regarding drag characteristics, lift-curve slope, and longitudinal stability parameter are provided.
Date: October 19, 1956
Creator: Swihart, John M.
System: The UNT Digital Library
Revision of the Wood Rats of the Genus Neotoma (open access)

Revision of the Wood Rats of the Genus Neotoma

From introduction: "Result of a study of the wood rats in the collection of the Biological Survey, numbering over 3,000 specimens, including topotypes of most of the species."
Date: October 19, 1910
Creator: Goldman, Edward A.
System: The UNT Digital Library
Wave Functions for Antishielding Factors of Ions and for the Electronic Polarisabilities of the Alkali Atoms (open access)

Wave Functions for Antishielding Factors of Ions and for the Electronic Polarisabilities of the Alkali Atoms

The purpose if this paper is to present tables of perturbed wave functions which have been obtained in three recent investigations: (1) wave functions v1'(nℓ→ℓ') which pertains to the perturbation of the d electrons of various ions as a result of the potential due to a nuclear quadrupole moment Q3 (2) wave functions v1',H(nℓ→ℓ) which represent the antishielding of the d electrons for a possible nuclear hexadecapole moment H; (3) wave functions u2'(ns→p) which pertain to the dipole perturbation of the valence (ns) electrons of the alkali atoms. Throughout this paper, the notation is the same as in a previous report in which a similar tabulation of perturbed wave function was made.
Date: October 19, 1962
Creator: Sternbeiner R. M.
System: The UNT Digital Library
A Rotating Source for Calibration Purposes (open access)

A Rotating Source for Calibration Purposes

This paper discusses a remotely operated system developed to transport (raise and lower) a 1/2 gram radium gamma radiation source for calibration of the HAPO film badges and finger rings. The system employs the rotometer principle for positioning the source for operating purposes. An accurate timer is utilized to assure the desired exposure time.
Date: October 19, 1959
Creator: Kocher, L. F.
System: The UNT Digital Library
Estimation of Reaction and Heat Release Rates for Graphite Oxidation (open access)

Estimation of Reaction and Heat Release Rates for Graphite Oxidation

A literature study has been made of rates for the reaction of oxygen with high-purity artificial graphite. Values from a number of sources have been expressed on a common basis which provides approximate correction for the retarding effects of oxygen diffusion in the graphite pores. The corrected rates can be correlated by the equation k = 7.24 x 10^9 exp (-22 100/T), where k has units of weight fraction oxidized per hour and T as in °K. Effects of oxygen concentration, solid and gas-phase contaminants, and radiation on the observed rates are discussed. Methods for estimating rates and spatial distribution of heat release during graphite oxidation are presented. These should be of value in analyzing the hazard of a graphite fire following a coolant system rupture in a gas-cooled, graphite-moderated reactor.
Date: October 19, 1960
Creator: Prados, John W.
System: The UNT Digital Library