Resource Type
Serial/Series Title
NACA Research Memorandums
136
Atomic Energy Commission Reports
52
Oak Ridge National Laboratory Reports
26
Hanford Works Reports
25
NACA Technical Reports
23
HW (Series)
18
University of California Radiation Laboratory Reports
17
AEC research and development report
11
ORNL (Series)
11
Ames Laboratory, Iowa State University (IS)
10
56 More
Country
Month
Day
308 Matching Results
Results open in a new window/tab.
Results:
1 - 24 of
308
next
Basic Magnetic Quantities and the Measurement of the Magnetic Properties of Materials
From Introduction: "The work of the Magnetic Measurements Section of the National Bureau of Standards includes (1) testing of specifically prepared test specimens intended for use as standards for checking magnetic testing apparatus (2) investigation and development of magnetic testing apparatus (3) calibration of mutual inductors, test coils, and instruments for measuring magnetic fields, and (4) investigations in the field of magnetics such as studies of phenomena associated with nuclear magnetic resonance or the selection and testing of materials suitable to be used as standards of magnetic susceptibility."
Date:
May 21, 1962
Creator:
Sanford, Raymond L. & Cooter, Irvin L.
Object Type:
Report
System:
The UNT Digital Library
Conductive Flooring for Hospital Operating Rooms
Report issued by the Bureau of Standards over studies on the importance of conductive flooring in hospitals. Types of conductive flooring are compared, and tested. The methods and results are presented, and discussed. This report includes tables, illustrations, and photographs.
Date:
March 21, 1960
Creator:
Boone, Thomas H.; Hermach, Francis L.; MacArthur, Edgar H. & McAuliff, Rita C.
Object Type:
Report
System:
The UNT Digital Library
Turbine Failure Investigation of J65-W-4 Turbojet Engine in an Altitude Test Chamber
Memorandum presenting an altitude investigation to determine the basic mechanism by which J65-W-4 turbine rotor-blade failures were occurring in service. The engine was installed in an altitude test chamber and a series of controlled engine throttle bursts, with and without inlet-air distortion, over a range of altitudes, flight Mach numbers, and inlet-air temperatures. An examination of the data obtained during the investigation indicated that the danger of turbine failure could be eliminated without any appreciable sacrifice in engine acceleration time.
Date:
September 21, 1956
Creator:
McAulay, John E.; Braithwaite, Willis M. & Ciepluch, Carl C.
Object Type:
Report
System:
The UNT Digital Library
A Wind-Tunnel Investigation of the Wing Loads Due to Deflected Inboard Ailerons on a 45 Degree Sweptback Wing at Transonic Speeds
Memorandum presenting the effects of deflected inboard ailerons on the wing loads of a 45 degree sweptback wing-body combination in the 16-foot transonic tunnel. The model had a wing with an aspect ratio of 3, a taper ratio of 0.2, and NACA 65A004 airfoil sections. Results regarding the chordwise pressure distributions, effect of ailerons on wing section loadings, effect of aileron on wing loading, and effects of a deflected aileron on opposite-wing loading are provided.
Date:
July 21, 1958
Creator:
Heath, Atwood R., Jr. & Igoe, Ann W.
Object Type:
Report
System:
The UNT Digital Library
An Investigation of the Dynamic and Static Stability Characteristics of a Group of Specialized Store Configurations at Transonic Speeds
Report presenting an investigation in the transonic tunnel to determine the dynamic and static stability characteristics of the Mark-6, Mark-4, TX-13, and Mark-5 special weapons and the effects of modifications of them for a range of Mach numbers.
Date:
August 21, 1953
Creator:
Henry, Beverly Z., Jr. & Braden, John A.
Object Type:
Report
System:
The UNT Digital Library
Preliminary Aerodynamic Data Pertinent to Manned Satellite Reentry Configurations
Report presenting some experimental data and calculations for a variety of aerodynamic shapes considered for use as manned reentry vehicles. Three types of vehicles were tested: non-lifting bodies, lifting bodies, and airplane-like vehicles. All of the configuration types were found to be suitable for use as manned reentry vehicles with certain fin and flap modifications for certain shapes.
Date:
July 21, 1958
Creator:
Penland, Jim A. & Armstrong, William O.
Object Type:
Report
System:
The UNT Digital Library
Wind-Tunnel Investigation of the Effect of Spin on the Aerodynamic Characteristics of a 60-Millimeter T-24 Mortar Shell With Several Tail-Fin Configurations
Report discussing an investigation to determine the effect of spin on the aerodynamic characteristics of the Army Ordnance Corps 60-millimeter T-24 mortar shell with several tail-fin configurations. Tests were performed at several airspeeds, speeds of rotation, and angles of attack. Under all test conditions, the models were statistically stable and the yawing moment increased with speed of rotation at higher angles of attack.
Date:
March 21, 1957
Creator:
Kemp, William B., Jr. & Hayes, William C., Jr.
Object Type:
Report
System:
The UNT Digital Library
NACA: University Conference on Aerodynamics: A Compilation of the Papers Presented
This document contains reproductions of the technical papers presented at the NACA - University Conference on Aerodynamics held at the Langley Aeronautical Laboratory on June 21, 22, and 23, 1948. The conference was held in recognition of the difficulties, imposed by security restrictions, in keeping abreast of the rapid advances in aerodynamics. The papers were prepared to review the status of a number of fields of interest, to summarize the more important wartime advances that are no longer classified, and to orient reference material for further study.
Date:
1948-06-21/1948-06-23
Creator:
unknown
Object Type:
Report
System:
The UNT Digital Library
Analysis of a Pneumatic Probe for Measuring Exhaust-Gas Temperatures with Some Preliminary Experimental Results
"A pneumatic probe based on continuity of mass flow through two restrictions separated by a cooling chamber was constructed to measure gas temperature at and beyond the limit of thermocouples. This probe consisted of a subsonic flat-plate orifice for the first restriction and a sonic-flow converging-diverging nozzle for the second restriction. The effect of variation in gas constants on the calibration is examined for common engine-exhaust gases" (p. 1).
Date:
May 21, 1952
Creator:
Scadron, Marvin D.
Object Type:
Report
System:
The UNT Digital Library
Investigation of Static Pressures and Boundary-Layer Characteristics on the Forward Parts of Nine Fuselages of Various Cross-Sectional Shapes at M Infinity Equal 2.01
Memorandum presenting an investigation in the supersonic pressure tunnel at a free-stream Mach number of 2.01 and at angles of attack up to 15 degrees of the static pressures and boundary-layer characteristics on the forward parts of nine fusleages of various cross-sectional shapes. Results regarding the static pressure distributions, boundary-layer characteristics, and selection of fuselage shapes for use with top-mounted scoop inlets are provided.
Date:
January 21, 1957
Creator:
Hasel, Lowell E. & Kouyoumjian, Walter L.
Object Type:
Report
System:
The UNT Digital Library
Buffet Tests of an Attack-Airplane Model With Emphasis on Analysis of Data From Wind-Tunnel Tests
Memorandum presenting the buffet characteristics of a scale model of an attack airplane over a range of Mach numbers. The wing had a modified delta plan form with an NACA 0008 airfoil section at the root and an NACA 0005 airfoil section at the tip, a leading-edge sweep of 41.11 degrees, an aspect ratio of 2.91, and a taper ratio of 0.226. Results regarding the frequency spectrum of bending moment, effect of density on root-mean-square bending moment, system damping coefficients, and buffet input force are provided.
Date:
February 21, 1958
Creator:
Davis, Don D., Jr. & Wornom, Dewey E.
Object Type:
Report
System:
The UNT Digital Library
Performance Comparison at Mach Numbers 1.8 and 2.0 of Full Scale and Quarter Scale Translating-Spike Inlets
"The performance of a full-scale translating-spike inlet was obtained at Mach numbers of 1.8 and 2.0 and at angles of attach from 0 deg to 6 deg. Comparisons were made between the full-scale production inlet configuration and a geometrically similar quarter-scale model. The inlet pressure-recovery, cowl pressure-distribution, and compressor-face distortion characteristics of the full-scale inlet agreed fairly well with the quarter-scale results" (p. 1).
Date:
October 21, 1957
Creator:
Hearth, Donald P.; Anderson, Bernhard H. & Dryer, Murray
Object Type:
Report
System:
The UNT Digital Library
Performance of Twin-Duct Variable-Geometry Side Inlets at Mach Numbers of 1.5 to 2.0
Report presenting testing of the performance of a twin-duct air-intake system mounted on the sides of a 1/8-scale fuselage forebody model of a proposed aircraft at several Mach numbers, angles of attack, and yaw. Results regarding the inlet survey, compression-surface boundary-layer removal and effects of second-ramp position, instability, effect of cant on inlet performance, inlet performance with 0 and 30 degree second ramp angles, performance with fixed second-ramp angles, and effect of canards are provided.
Date:
January 21, 1957
Creator:
Yeager, Richard A.; Beheim, Milton A. & Klann, John L.
Object Type:
Report
System:
The UNT Digital Library
Hydrodynamic Characteristics of a Low-Drag, Planing-Tail Flying-Boat Hull
Report discussing the hydrodynamic characteristics of a flying boat with a low-drag, planing-tail hull compared with a conventional-type hull. The planing-tail model had more take-off stability than the conventional model and had lower hydrodynamic resistance. Information about the landing stability, variation of trim with speed, and spray characteristics is also provided.
Date:
October 21, 1948
Creator:
Suydam, Henry B.
Object Type:
Report
System:
The UNT Digital Library
Altitude Starting Tests of a Small Solid Propellant Rocket
From Summary: "Four solid-propellant rocket engines of nominal 500-pound thrust were tested for starting characteristics at pressure altitudes ranging from 89,000 to 111,000 feet and at a temperature of -75^o F. Chamber pressures were measured on two of the runs. Average chamber pressures in these two runs were lower than expected, although action times agreed with the expected values."
Date:
June 21, 1957
Creator:
Sloop, John L. & Krawczonek, Eugene M.
Object Type:
Report
System:
The UNT Digital Library
Determination of Shapes of Boattail Bodies of Revolution for Minimum Wave Drag
"By use of an approximate equation for the wave drag of slender bodies of revolution in a supersonic flow field, the optimum shapes of certain boattail bodies are determined for minimum wave drag. The properties of three specific families of bodies are determined, the first family consisting of bodies having a given length and base area and a contour passing through a prescribed point between the nose and base, the second family having fixed length, base area, and maximum area, and the third family having given length, volume, and base area. The method presented is easily generalized to determine minimum-wave-drag profile shapes which have contours that must pass through any prescribed number of points" (p. 1).
Date:
August 21, 1951
Creator:
Adams, Mac C.
Object Type:
Report
System:
The UNT Digital Library
Simplified Theory for Dynamic Relation of Ramjet Pressures and Fuel Flow
Memorandum presenting an analysis to determine, for control design purposes, the approximate response of pressures in the ramjet engine to changes in fuel flow. In the first part, the response after dead time is treated by the linearized lumped-parameter method. In the second, the dead time occurring between the change in fuel flow and the beginning of the pressure response is discussed.
Date:
October 21, 1957
Creator:
Hurrell, Herbert G.
Object Type:
Report
System:
The UNT Digital Library
Experimental investigation at supersonic speeds of twin-scoop duct inlets of equal area I : an inlet enclosing 61.5 percent of the maximum circumference of the forebody
Report presenting tests at Mach numbers between 1.36 and 2.01 of a twin-scoop air intake enclosing 61.5 percent of the maximum circumference of a body of revolution and located five forebody diameters behind the apex, which showed that the total pressure recovered after diffusion was about 10 percent greater than that attained in previous tests with an annular entrance of the same area.
Date:
January 21, 1948
Creator:
Davis, Wallace F. & Goldstein, David L.
Object Type:
Report
System:
The UNT Digital Library
High-Speed Wind-Tunnel Tests of a Model Pursuit Airplane and Correlation With Flight-Test Results
Report presenting the results of tests on a model of a jet-propelled airplane and a comparison of drag, maximum lift coefficient, and elevator angle required for level flight in the wind tunnel and in flight. Results regarding the aerodynamic characteristics, longitudinal control, wing pressure distribution, and dive-recovery flaps are provided.
Date:
January 21, 1948
Creator:
Cleary, Joseph W. & Gray, Lyle J.
Object Type:
Report
System:
The UNT Digital Library
Calculations of the Supersonic Wave Drag of Nonlifting Wings with Arbitrary Sweepback and Aspect Ratio: Wings Swept Behind the Mach Lines
"On the basis of a recently developed theory for finite sweptback wings at supersonic speeds, calculations of the supersonic wave drag at zero lift were made for a series of wings having thin symmetrical biconvex sections with untapered plan forms and various angles of sweepback and aspect ratios. The results are presented in a unified form so that a single chart permits the direct determination of the wave drag for this family of airfoils for an extensive range of aspect ratio and sweepback angle for stream Mach numbers up to a value corresponding to that at which the Mach line coincides with the wing leading edge. The calculations showed that in general the wave-drag coefficient decreased with increasing sweepback" (p. 1).
Date:
February 21, 1947
Creator:
Harmon, Sidney M. & Swanson, Margaret D.
Object Type:
Report
System:
The UNT Digital Library
Performance of Experimental Turbojet-Engine Combustor 1: Performance of a One-Eighth Segment of an Experimental Turbojet-Engine Combustor
Report presenting an investigation of a one-eighth segment of an annular combustor suitable for use as a component of an experimental turbojet engine. Due to the small space available for the combustor, a special design involving a minimum of obstructions in the combustion chamber was created. Results regarding the temperature-rise efficiency, total-pressure loss, and exhaust-gas temperature variation for several simulated engine operating conditions are provided.
Date:
April 21, 1948
Creator:
Hill, Francis U. & Mark, Herman
Object Type:
Report
System:
The UNT Digital Library
Preliminary correlation of efficiency of aircraft gas-turbine combustors for different operating conditions
Report presenting a correlation of combustion-efficiency data obtained in experimental investigations with 14 aircraft gas-turbine combustors. The precision is not good for some combustors, but can help in predicting the efficiency at different operating conditions and in comparing the performance of different combustors from data obtained in unrelated tests.
Date:
September 21, 1950
Creator:
Childs, J. Howard
Object Type:
Report
System:
The UNT Digital Library
Internal film cooling experiments in 4-inch duct with gas temperatures to 2000 degrees F
Report presenting an investigation of the cooling effectiveness of water films on the inner surface of a well-insulated, 4-inch-diameter duct with air flowing through the duct at a range of temperature and Reynolds numbers. Results regarding the effect of the gas temperature and mass velocity on liquid-cooled length, effect of coolant flow on liquid-cooled length, and some suggestions for further investigation are provided. Equations for correlation are created from the data.
Date:
September 21, 1950
Creator:
Kinney, George R. & Sloop, John L.
Object Type:
Report
System:
The UNT Digital Library
Some Effects of Chordwise Fences on the Aerodynamic Characteristics of Four Moderately Sweptback Wings in the Low-Lift Range at Transonic Mach Numbers and at Mach Number 1.9
Report presenting a study of data from wind-tunnel investigations to determine the effects of thin chordwise fences on some of the aerodynamic characteristics of four moderately sweptback wings at a low-lift range. The fences caused no large detrimental effects on lift or pitching moment at transonic or supersonic speeds. Results regarding the increment of drag coefficient due to fences, effect of fences on the lift coefficient and longitudinal stability, and effects on aileron effectiveness are provided.
Date:
July 21, 1950
Creator:
Guy, Lawrence D.
Object Type:
Report
System:
The UNT Digital Library