Resource Type
Serial/Series Title
NACA Research Memorandums
154
Atomic Energy Commission Reports
67
University of California Radiation Laboratory Reports
25
Hanford Works Reports
23
NACA Technical Reports
21
Oak Ridge National Laboratory Reports
13
UCRL (Series)
13
HW (Series)
11
Report (U.S. Atomic Energy Commission)
11
AEC research and development report
10
52 More
Country
States
Decade
Month
Day
329 Matching Results
Results open in a new window/tab.
Results:
1 - 24 of
329
next
Chemistry of Cement: Proceedings of the Fourth International Symposium, Washington 1960, Volume 2
From Synopsis: "This paper deals mainly with cement paste in terms of its porosity, internal surface area, interaction between solid substance and evaporable water and related properties."
Date:
September 27, 1962
Creator:
United States. Bureau of Standards.
Object Type:
Report
System:
The UNT Digital Library
A System for the Automatic Computation of Disintegration Rates From Radiochemical Data
From Abstract: "Automatic computation of these general formulas from raw data and procedures for their adaption to a number of specific analyses are described."
Date:
May 27, 1959
Creator:
Collins, William R., Jr.
Object Type:
Report
System:
The UNT Digital Library
Preliminary Data on Fallout From the Fall 1961 USSR Test Series: Staff Report
From introduction: "Following the USSR announcement of its intention to resume testing, arrangements were made for the three stations collecting individual rainfall samples to begin analyses for short-lived nuclides. Some of the data are now available and are reported here." From Data: "The available data, including samples for Houston, Texas and Louisville, Kentucky are given in the tables at the end of this report."
Date:
February 27, 1962
Creator:
U.S. Atomic Energy Commission. Health and Safety Laboratory.
Object Type:
Report
System:
The UNT Digital Library
Hydrodynamic Characteristics of Missiles Launched Under Water
Report presenting some of the hydrodynamic problems associated with launching an air missile from underwater. The results of an experiment with models are also provided, including deviation angle, effect of forward speed of the submarine, curved path of the missile, and potential environmental disruptions.
Date:
June 27, 1958
Creator:
Dawson, John R.
Object Type:
Report
System:
The UNT Digital Library
Analysis of turbojet and ram-jet engine cycles using various fuels
From Introduction: "These data have been collected for presentation in this report to illustrate the performance of turbojet and ram-jet cycles utilizing several of the more promising high-energy fuels. Results are presented in terms of engine over-all efficiency and thrust per pound of airflow as functions of flight Mach number."
Date:
November 27, 1956
Creator:
Wilcox, E. Clinton; Weber, Richard J. & Tower, Leonard K.
Object Type:
Report
System:
The UNT Digital Library
Effects of Wing-Fuselage Flow Fields on Missile Loads at Subsonic Speeds
"The flow-field characteristics around a swept-wing airplane model at low subsonic speed are described, and the loads induced on a typical missile model while operating within these flow fields are presented. In addition, theoretical flow fields are compared with experiment and are used in first-order estimations of the resulting induced missile loads" (p. 1).
Date:
June 27, 1955
Creator:
Alford, William J., Jr.
Object Type:
Report
System:
The UNT Digital Library
Comparison of Experimental and Theoretical Zero-Lift Wave-Drag Results for Various Wing-Body-Tail Combinations at Mach Numbers Up to 1.9
"Comparisons are made of experimental and theoretical zero-lift wave drag for several nose shapes, wing-body combinations, and models of current airplanes at Mach numbers up to 1.0. The experimental data were obtained from tests in the Ames 6- by 6-foot supersonic wind tunnel and at the NACA Wallops Island facility. The theoretical drag was found by use of linear theory utilizing model area distributions" (p. 1).
Date:
March 27, 1957
Creator:
Petersen, Robert B.
Object Type:
Report
System:
The UNT Digital Library
Tests of the Northrop XB-62 Missile in the Ames 40- by 80-Foot Wind Tunnel
Memorandum presenting a series of tests made on a full-scale Northrop XB-62 missile to determine the cause of a directional out-of-trim condition which was encountered on the initial missile flight tests. The results indicated that the directional out-of-trim condition was caused by aerodynamic loads induced by engine operation.
Date:
September 27, 1954
Creator:
Graham, David
Object Type:
Report
System:
The UNT Digital Library
Compilation and Analysis of U.S. Turbojet and Ram-Jet Engine Characteristics
Report presenting a compilation of sea-level static and flight-performance data for existing and designed U.S. axial-flow turbojet and ram-jet engines. Factors considered include engine size, performance, and weight, and actual and theoretical performances are compared.
Date:
November 27, 1956
Creator:
Cesaro, Richard S. & Walker, Curtis L.
Object Type:
Report
System:
The UNT Digital Library
Maneuver Performance of Interceptor Missiles
"From these preliminary wind-tunnel tests of interceptor missile configurations and the analysis of point defense against ballistic missiles, it is concluded that adequate aerodynamic lift is readily available and should be utilized when operating under high-dynamic-pressure conditions and that more work should be done on controls, either aerodynamic or reaction type, so that the configurations may be trimmed to the angles of attack required to develop the necessary turning force" (p. 5).
Date:
June 27, 1958
Creator:
Stone, David G.
Object Type:
Report
System:
The UNT Digital Library
Experimental Investigation of Average Heat-Transfer and Friction Coefficients for Air Flowing in Circular Tubes Having Square-Thread-Type Roughness
"An investigation of forced-convection heat transfer and associated pressure drops was conducted with air flowing through electrically heated Inconel tubes having various degrees of square-thread-type roughness, an inside diameter of 1/2 inch, and a length of 24 inches were obtained for tubes having conventional roughness ratios (height of thread/radius of tube) of 0 (smooth tube), 0.016, 0.025, and 0.037 over ranges of bulk Reynolds numbers up to 350,000, average inside-tube-wall temperatures up to 1950deg R, and heat-flux densities up to 115,000 Btu per hour per square foot" (p. 1).
Date:
June 27, 1952
Creator:
Sams, Eldon W.
Object Type:
Report
System:
The UNT Digital Library
Supplementary Investigation in the Langley 20-Foot Free-Spinning Tunnel of a 1/20-Scale Model of the Douglas F4D-1 Airplane With External Wing Fuel Tanks
Report presenting an investigation in the 20-foot free-spinning tunnel on a scale model to determine the spin and recovery characteristics of the Douglas F4D-1 airplane equipped with external fuel tanks. Results regarding erect spins, inverted spins, and parachute results are provided.
Date:
December 27, 1957
Creator:
Bowman, James S., Jr.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic Principles for the Design of Jet-Engine Induction Systems
Jet engine induction systems investigations and relationship of air inlets, drag, airframe, pressure recovery, flow and interferences.
Date:
February 27, 1956
Creator:
Davis, Wallace F. & Scherrer, Richard
Object Type:
Report
System:
The UNT Digital Library
Presentation on Facility Problems in High-Temperature Structures Research
"This presentation is intended to reflect the current general approach of the NACA to the problems of high-temperature structures research facilities. The facilities and problems discussed apply to flight in the Mach number range from 2 to about 20. It is emphasized that this field is one in which the thinking is rapidly changing and the facilities investigations discussed, particularly for the higher temperature range, are in the exploratory stage" (p. 1).
Date:
March 27, 1956
Creator:
Purser, Paul E. & Heldenfels, Richard R.
Object Type:
Report
System:
The UNT Digital Library
Chemical and Physical Properties of a Boron-Carbon-Hydrogen Fuel Z-244 (NACA 55Z8)
Report presenting chemical and physical properties determined from a sample of boron-carbon-hydrogen fuel Z-244.
Date:
March 27, 1956
Creator:
Spakowski, A. E.; Cramer, Patricia M. & Buddie, Marianne
Object Type:
Report
System:
The UNT Digital Library
Some Effects of Roll Rate on the Longitudinal Stability Characteristics of the Hughes Falcon Missile, ''C'' Configuration, for a Mach Number Range of 1.1 to 1.8 as Determined From Flight Test
Report discussing testing of a Hughes Falcon missile, C configuration, to determine the stability and control characteristics of the missile while rolling. Information about the time histories, normal force due to angle of attack, pitching moment due to angle of attack, damping, and control effectiveness is provided.
Date:
December 27, 1955
Creator:
Lundstrom, Reginald R. & Baber, Hal T., Jr.
Object Type:
Report
System:
The UNT Digital Library
Comparison and Evaluation of Two Model Techniques Used in Predicting Bomb-Release Motions
"For the purpose of calculating bomb trajectories, forces and moments have been measured on bombs of three fineness ratios in the presence of a swept-wing fighter-bomber configuration at a Mach number of 1.61. Trajectories thus obtained have been compared with those from dynamic model tests and an analysis has been made to determine the source of errors and to suggest improvements in both techniques."
Date:
December 27, 1957
Creator:
Carlson, Harry W.; Geier, Douglas J. & Lee, John B.
Object Type:
Report
System:
The UNT Digital Library
Analysis of a liquid-metal turbine-propeller cycle for propulsion of low-speed nuclear- powered aircraft
From Introduction: "The intermediate subsonic speed range is considered and the liquid-metal turbine-propeller cycle discussed in this report. In this report, compressor pressure ratio, heat-exchanger air-inlet Mach number, and turbine-inlet temperature were optimized for maximum engine net thrust per engine-plus-heat exchanger weight (minimum airplane gross weight) for a range of heat-exchanger effective wall temperature."
Date:
May 27, 1952
Creator:
Rom, F. E. & Wachtl, W. W.
Object Type:
Report
System:
The UNT Digital Library
Pressure Measurements on an Afterbody Behind Various Blunt Nose Shapes at a Mach Number of 2
Memorandum presenting an investigation of flow surrounding afterbodies behind blunt nose shapes at a Mach number of 2 in the 27- by 27-inch preflight jet. Pressure measurements were made on and around the afterbodies for each configuration.
Date:
December 27, 1957
Creator:
Speegle, Katherine C.
Object Type:
Report
System:
The UNT Digital Library
Influence of Combustion-chamber Length on Afterburner Performance
Memorandum presenting an investigation of the influence of combustion-chamber length on afterburner performance under conditions simulating altitude flight. Results regarding afterburner-inlet conditions, operational limits, and structural cooling requirements are provided.
Date:
August 27, 1954
Creator:
Useller, James W.; Braithwaite, Willis M. & Rudey, Carl J.
Object Type:
Report
System:
The UNT Digital Library
On the flying qualities of helicopters
Report presenting the flying qualities problems of current helicopters, including instability with angle of attack in forward flight, control sensitivity in hovering, and control forces following control movement in maneuvers. Some possible solutions to these issues are presented.
Date:
January 27, 1949
Creator:
Reeder, John P. & Gustafson, F. B.
Object Type:
Report
System:
The UNT Digital Library
Reflection of a Weak Shock Wave From a Boundary Layer Along a Flat Plate 1: Interaction of Weak Shock Waves With Laminar and Turbulent Boundary Layers Analyzed by Momentum-Integral Method
Note presenting an investigation of the phenomena encountered when a plane oblique shock wave is incident upon the boundary layer of a flat plate. The flow field was divided into a viscous layer near the wall and a supersonic potential outer flow. With the outer flow determined, boundary-layer growth and pressure distribution were computed and results for the laminar cases were obtained and provided.
Date:
January 27, 1953
Creator:
Ritter, Alfred & Kuo, Yung-Huai
Object Type:
Report
System:
The UNT Digital Library
Low-Speed Investigation of a Small Triangular Wing of Aspect Ratio 2.0 1 The Effect of Combination With a Body Revolution and Height Above a Ground Plane
Memorandum presenting low-speed wind-tunnel test conducted of a triangular wing of aspect ratio 2.0 with a symmetrical double-wedge section with a maximum thickness of 5 percent of the chord at 20 percent of the chord. The wing was also tested in the presence of a ground plane. Results regarding isolated wing and wing-body combinations, split-flap effectiveness, and ground effect are provided.
Date:
August 27, 1948
Creator:
Rose, Leonard M.
Object Type:
Report
System:
The UNT Digital Library
High-speed aerodynamic characteristics of horn and overhang balances on a full-scale elevator
Report presenting high-speed wind tunnel testing of horn- and overhang-balance elevators on a full-scale, semispan, horizontal tail. The effects of unshielding the horn and unsealing the overhang were investigated. Results regarding aerodynamic characteristics, distortions of the tail, and critical Mach numbers are provided.
Date:
February 27, 1948
Creator:
Cleary, Joseph W. & Krumm, Walter J.
Object Type:
Report
System:
The UNT Digital Library