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NACA Research Memorandums
183
Atomic Energy Commission Reports
63
Hanford Works Reports
26
Oak Ridge National Laboratory Reports
26
NACA Technical Reports
24
University of California Radiation Laboratory Reports
21
HW (Series)
16
ORNL (Series)
12
AEC research and development report
10
BMI (Series)
8
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1024 Channel Time-of-Flight Analyzer for MTR Fast Chopper - Operating Manual
Report on the principle of measuring the time-of-flight of neutrons, magnetic-core storage of detector pulses, how pulses are stored, current generator, storage cycle generator, and cathode ray oscillograph.
Date:
March 11, 1959
Creator:
Petree, F. L.
Object Type:
Report
System:
The UNT Digital Library
Advanced Designs and Special Applications for Fast Breeders
The purpose of this paper is to describe a few of the suggested advanced concepts for fast breeder reactors and to compare these with the standard approach as to their potential advantage. I have attempted to estimate the economic effect of full technical success with each of the proposed concepts. The proposed concepts include: (1) single sodium system, (2) steam-cooled core concept, (3) direct cycle reactor using potassium as reactor coolant and working fluid, (4) molten plutonium-fuel alloy circulated and cooled by a jet of sodium, (5) settled-bed core, (6) molten salt concept, and (7) paste-fuel system.
Date:
November 11, 1963
Creator:
Hammond, R. Philip
Object Type:
Report
System:
The UNT Digital Library
Aerial Radiometric and Magnetic Survey: Trona National Topographic Map, California. Volume 1
The results of analyses of the airborne gamma radiation and total magnetic field survey flown for the region identified as the Trona National Topographic Map NI-11-12 is presented in Volume I and II of this report. This volume gives the description of the program and the results.
Date:
December 11, 1978
Creator:
High Life Helicopters, Inc.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic Characteristics of a 0.04956-Scale Model of the Convair F-102A Airplane at Transonic Speeds
"Tests have been conducted in the Langley 8-foot transonic tunnel on a 0.04956-scale model of the Convair F-102A airplane which employed an indented and extended fuselage, cambered wing leading edges, and deflected wing tips. Force and moment characteristics were obtained for Mach numbers from 0.60 to 1.135 at angles of attack up to 20 degrees. In addition, tests were made over a limited angle-of-attack range to determine the effects of the cambered leading edges, deflected tips, and a nose section with a smooth area distribution" (p. 1).
Date:
April 11, 1955
Creator:
Tempelmeyer, Kenneth E. & Osborne, Robert S.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic Characteristics of a Circular Cylinder at Mach Number 6.86 and Angles of Attack Up to 90 Degrees
"Pressure-distribution and force tests of a circular cylinder have been made in the Langley 11-inch hypersonic tunnel at a Mach number of 6.86, a Reynolds number of 129,000 based on diameter, and angles of attack up to 90 degrees. The results are compared with the hypersonic approximation of Grimminger, Williams, and Young and with a simple modification of the Newtonian flow theory. The comparison of experimental results shows that either theory gives adequate general aerodynamic characteristics but that the modified Newtonian theory gives a more accurate prediction of the pressure distribution" (p. 1).
Date:
March 11, 1954
Creator:
Penland, Jim A.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic characteristics of a flying-boat hull having a length-beam ratio of 15 and a warped forebody
From Introduction: "The results of two phases of this investigation, presented in references 1 and 2, have indicated possible ways of reducing hull drag without causing large changes in aerodynamic stability and hydrodynamic performance."
Date:
February 11, 1949
Creator:
MacLeod, Richard G.
Object Type:
Report
System:
The UNT Digital Library
The aerodynamic characteristics of a supersonic aircraft configuration with a 40 degree sweptback wing through a Mach number range from 0 to 2.4 obtained from various sources
"A summary and analysis have been made of the results of various investigations to determine the aerodynamic characteristics of a supersonic aircraft configuration. The configuration has a wing with 40 degree sweepback at the quarter-chord line, aspect ratio 4, taper ratio 0.5, and 10-percent-thick circular-arc sections normal to the quarter-chord line. Experimental data were available for a Mach number range from 0.16 to 2.32. Results obtained from wing-flow, rocket-model, transonic-bump, and tunnel tests are presented and, where possible, are supplemented by empirical and theoretical calculations" (p. 1).
Date:
April 11, 1952
Creator:
Spearman, M. Leroy & Robinson, Ross B.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic Design of Axial-flow Compressors 6 - Experimental Flow in Two-Dimensional Cascades
"Available experimental two-dimensional cascade data for conventional compressor blade sections are correlated at a reference incidence angle in the region of minimum loss. Variations of reference incidence angle, total-pressure loss, and deviation angle with cascade geometry, inlet Mach number, and Reynolds number are investigated. From the analysis and the correlations of the available data, rules and relations are evolved for the prediction of blade-profile performance" (p. 1).
Date:
November 11, 1955
Creator:
Lieblein, Seymour
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic heating of a wing as determined from a free-flight rocket-model test to Mach number 3.64
From Introduction: "The primary purpose of the wing instrumentation was to obtain data for use in design of NACA research missiles; however, it is believed that the wing is representative of typical supersonic designs and that the data will be of general use and interest. Only the wing data are reported herein."
Date:
September 11, 1956
Creator:
Swanson, Andrew G. & Rumsey, Charles B.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic Heating of Blunt Nose Shapes at Mach Numbers Up to 14
From Introduction: "The importance of blunt noses as a means of reducing the heat transfer to high velocity missiles has recently received much publicity. The question of just what blunt shape is best is still moot, and it is the purpose of this paper to present and examine some recent experimental results which may throw some light on this problem."
Date:
August 11, 1958
Creator:
Stoney, William E., Jr.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic heating of blunt nose shapes at Mach numbers up to 14
From Introduction: "The importance of blunt noses as a means of reducing the heat transfer to high velocity missiles has recently received much publicity. The question of just what blunt shape is best is still moot, and it is the purpose of this paper to present and examine some recent experimental results which may throw some light on the problem."
Date:
August 11, 1958
Creator:
Stoney, William E., Jr.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic Measurements Made During Navy Investigation of Human Tolerance to Wind Blasts
From Summary: "This report presents the aerodynamic measurements made during a Navy investigation conducted in the Langley 8-foot high speed tunnel to determine the actual human tolerance to wind blasts."
Date:
March 11, 1947
Creator:
Loving, Donald L.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees: Subsonic Mach and Reynolds number effects on the characteristics of the wing and on the effectiveness of an elevon
Report presenting a wind-tunnel investigation of a semispan model of a wing swept back 63 degrees with an aspect ratio of 3.5 and a taper ratio of 0.25. The tests were conducted to evaluate the effects of Reynolds and Mach number on the aerodynamic characteristics of the wing. Results regarding the characteristics of the wing with the elevon undeflected, effectiveness of the elevon, effects of roughness strips, and effect of model deflection under varying loads are provided.
Date:
October 11, 1948
Creator:
Reynolds, Robert M. & Smith, Donald W.
Object Type:
Report
System:
The UNT Digital Library
Airfoil section characteristics as affected by protuberances
From Introduction: "The present report deals with another phase of the investigation; that is, the effects on airfoil section characteristics of protuberances extending along the entire span from the airfoil surface."
Date:
July 11, 1932
Creator:
Jacobs, Eastman N.
Object Type:
Report
System:
The UNT Digital Library
Alternating Current and Square-Wave Polarography
A exploratory study was made of a polarographic technique in which an alternating sine or square-wave potential is superimposed upon the applied d.c. potential of the polarographic scan. Recording of the a.c. component of the polarographic current results in derivative-type waves. It was shown that the technique yields greater sensitivity and greater selectivity than normal polarographic technique.
Date:
September 11, 1956
Creator:
Hamm, Randall E.
Object Type:
Report
System:
The UNT Digital Library
Altitude performance characteristics of tail-pipe burner with variable-area exhaust nozzle
From Introduction: "Data are presented to show the effects of tail-pipe fuel-air ratio, altitude, and flight Mach number on tail-pipe-burner performance at rated engine speed and approximately constant turbine-outlet temperature. Operational characteristics of the tail-pipe burner and variable-area exhaust nozzle are also reported."
Date:
August 11, 1950
Creator:
Jansen, Emmert T. & Thorman, H. Carl
Object Type:
Report
System:
The UNT Digital Library
Altitude-Wind-Tunnel Investigation of Oil-System Performance of XR-4360-8 Engine in XTB2D-1 Airplane
"An investigation was conducted in the Cleveland altitude wind tunnel to determine the aerodynamic characteristics and the oil delivery critical altitude of the oil-cooler installation of an XTB2D-1 airplane. The investigation was made with the propeller removed end with the engine operating at 1800 brake horsepower, an altitude of 15,000 feet (except for tests of oil-delivery critical altitude), oil-cooler flap deflections from -20 degrees to 20 degrees and inclinations of the thrust axis of 0 degrees, 1.5 degrees, and 6 degrees. At an inclination of the thrust axis of 0 degrees and with the propeller operating, the total-pressure recovery coefficient at the face of the oil cooler varied from 0.84 to 1.10 depending on the flap deflection" (p. 1).
Date:
October 11, 1946
Creator:
Conrad, E. William
Object Type:
Report
System:
The UNT Digital Library
Altitude-Wind-Tunnel Investigation of Performance of Several Propellers on YP-47M Airplane at High Blade Loading, 1, Aeroproducts H20C-162-X11M2 Four-Blade Propeller
"An investigation was made in the Cleveland Altitude wind tunnel to determine the performance of an Aeroproducts H20C-162-X11M2 four-blade propeller on a YP-47M airplane at high blade loadings and high engine powers. The propeller characteristics were obtained for a range of power coefficients from 0.30 to 1.00 at free-stream Mach numbers of 0.40 and 0.50. The results of the force measurements are indicative only of trends in propeller efficiency with changes in power coefficient and advance-diameter ratio because unknown interference effects existed during the investigation" (p. 1).
Date:
October 11, 1946
Creator:
Saari, Martin J. & Wallner, Lewis E.
Object Type:
Report
System:
The UNT Digital Library
Altitude-wind-tunnel investigation of thrust augmentation of a turbojet engine 3: performance with tail-pipe burning in standard-size tail pipe
From Introduction: "Evaluation of tail-pipe burning in this engine with a larger tail-pipe combustion chamber is discussed in reference 1. Results of investigations on tail-pipe burning in this engine at static sea-level conditions are presented in reference 2. An investigation of thrust augmentation by means of injecting water at the inlet of an axial-flow compressor engine is discussed in reference 3."
Date:
August 11, 1947
Creator:
Fleming, William A. & Golladay, Richard L.
Object Type:
Report
System:
The UNT Digital Library
An analysis of available data on effects of wing-fuselage-tail and wing-nacelle interference on the distribution of the air load among components of airplanes
From Introduction: "The purpose of the present paper is to summarize the available data on the effects of wing-fuselage-tail and wing-nacelle interference on the distribution of the air load among aircraft components. Some discussion is also given of the effects of center-of-gravity position."
Date:
April 11, 1949
Creator:
Wollner, Bertram C.
Object Type:
Report
System:
The UNT Digital Library
An analysis of base pressure at supersonic velocities and comparison with experiment
From Introduction: "The primary purpose of the investigation described in the present described in the present report is to formulate a method which is of value for qualitative calculations of base pressure both on airfoils and bodies."
Date:
May 11, 1951
Creator:
Chapman, Dean R.
Object Type:
Report
System:
The UNT Digital Library
Analysis of factors affecting selection and design of air-cooled single-stage turbines for turbojet engines 4: coolant-flow requirements and performance of engines using air-cooled corrugated-insert blades
Report presenting an investigation of the estimated minimum cooling requirements and related performance of turbojet engines equipped with high-performance single-stage turbines with air-cooled corrugated-insert blades over a range of turbine-inlet temperature, tip speed, and hub-tip radius ratio for Mach number 2 at 50,000 feet. The effects of stress-ratio factor, flight Mach number, altitude, turbine rotor impeller efficiency, and outside heat-transfer coefficient on cooling requirements were also investigated.
Date:
May 11, 1955
Creator:
Slone, Henry O. & Hubbartt, James E.
Object Type:
Report
System:
The UNT Digital Library
Analysis of Fully Developed Turbulent Heat Transfer at Low Peclet Numbers in Smooth Tubes With Application to Liquid Metals
From Introduction: "Analyses of heat transfer for liquid metals flowing turbulently in smooth tubes (low Pradtl numbers) are given in reference 1 and 2. The predicted heat-transfer coefficients from these analyses are considerably higher than those determined in the experimental heat-transfer investigations for mercury and lead bismuth given in references 2 to 4. If the analytical and experimental results for flow of gases are compared at low Peclet numbers, they are also found to be in disagreement (references 5 and 6)."
Date:
August 11, 1952
Creator:
Deissler, Robert G.
Object Type:
Report
System:
The UNT Digital Library
Analysis of Meteorological Data Obtained During Flight in a Supercooled Stratiform Cloud of High Liquid-Water Content
"Flight icing-rate data obtained in a dense and abnormally deep supercooled stratiform cloud system indicated the existence of liquid-water contents generally exceeding values in amount and extent previously reported over the midwestern sections of the United States. Additional information obtained during descent through a part of the cloud system indicated liquid-water contents that significantly exceeded theoretical values, especially near the middle of the cloud layer. The growth of cloud droplets to sizes that resulted in sedimentation from the upper portions of the cloud is considered to be a possible cause of the high water contents near the center of the cloud layer" (p. 1).
Date:
July 11, 1951
Creator:
Perkins, Porter J. & Kline, Dwight B.
Object Type:
Report
System:
The UNT Digital Library