Resource Type
Serial/Series Title
NACA Research Memorandums
151
Atomic Energy Commission Reports
74
NACA Technical Reports
32
Hanford Works Reports
19
University of California Radiation Laboratory Reports
19
Oak Ridge National Laboratory Reports
18
AEC research and development report
14
HW (Series)
10
Report (U.S. Atomic Energy Commission)
10
UCRL (Series)
9
59 More
Country
States
Month
Day
343 Matching Results
Results open in a new window/tab.
Results:
1 - 24 of
343
next
Semi-Empirical Method of Calculating the Energy-Absorption Build-up Factor with an Application to a Uniformly Contaminated Space Having Spherical Boundaries
From Abstract: "The results are compared with those obtained by other methods, and an application to the problem of uniformly and continuously distributed point-source is discussed."
Date:
October 14, 1957
Creator:
O'Brien, Keran; Lowder, Wayne M. & Solon, Leonard R.
Object Type:
Report
System:
The UNT Digital Library
Experimental Evaluation of the Fallout-Radiation Protection Afforded by a Southwestern Residence
Report regarding experiments made to determine the fallout-radiation protection offered by a "single-story stucco and frame house with a heavy shake roof and no basement," (p. 5) which is noted as being popular in the southwestern United States.
Date:
March 14, 1961
Creator:
Burson, Z.; Parry, D. & Borella, H.
Object Type:
Report
System:
The UNT Digital Library
Investigation of the Low-Speed Flight Characteristics of a 1/15-Scale Model of the Convair XB-58 Airplane
Report presenting an investigation of the low-speed stability and control characteristics of a 1/15-scale free-flying model of the Convair XB-58 airplane. Results regarding the longitudinal stability and control and a pod-drop investigation are provided.
Date:
November 14, 1957
Creator:
Paulson, John W.
Object Type:
Report
System:
The UNT Digital Library
Investigation of Control Effectiveness and Stability Characteristics of a Model of a Low-Wing Missile With Interdigitated Tail Surfaces at Mach Numbers of 2.29, 2.97, and 3.51
"A brief investigation of the longitudinal stability and control effectiveness at supersonic speeds of a model of a low-wing missile with interdigitated tail surfaces was made in the Langley Unitary Plan wind tunnel. The data were obtained at Mach numbers M of 2.29, 2.97, and 3.51 for Reynolds number (based on the mean geometric chord of the wing) of 1.15 x 10(exp 6), 1.14 x 10(exp 6), and 1.11 x 10(exp 6), respectively. Data were obtained for three settings of the longitudinal control surfaces: with deflection of all surfaces, with deflection of the lower surfaces only, and with all surfaces undeflected" (p. 1).
Date:
July 14, 1958
Creator:
Presnell, John G., Jr.
Object Type:
Report
System:
The UNT Digital Library
Effects of Boattail Area Contouring and Simulated Turbojet Exhaust on the Loading and Fuselage-Tail Component Drag of a Twin-Engine Fighter-Type Airplane Model
Effects of boattail area contouring and simulated turbojet exhaust on loading and fuselage-tail component drag of twin-engine fighter-type airplane model.
Date:
July 14, 1958
Creator:
Foss, Willard E., Jr.; Runckel, Jack F. & Lee, Edwin E., Jr.
Object Type:
Report
System:
The UNT Digital Library
Investigation of a 1/4 Scale Model of the Republic F-105 Airplane in the Langley 19-Foot Pressure Tunnel: Longitudinal Stability and Control and Horizontal-Tail Hinge-Moment and Normal-Force Characteristics of the Model Equipped With a Drooped Supersonic-Type Elliptical Wing-Root Inlet
Report presenting testing of the Republic F-105 at low speeds to determine the results of additional longitudinal stability tests of measurements of the hinge moments and normal force of the all-movable horizontal tail on a model equipped with a supersonic-type elliptical wing-root inlet.
Date:
November 14, 1955
Creator:
Cancro, Patrick A. & Kelly, H. Neale
Object Type:
Report
System:
The UNT Digital Library
Power-Off Tests of the Northrop N9M-2 Tailless Airplane in the 40- by 80-Foot Wind Tunnel
Report discussing tests on the N9M-2 airplane to evaluate the airplane efficiency factor and to investigate the characteristics of the aeroboost in the elevon control system. The efficiency factor compared reasonably well to conventional airplanes and the aeroboost system and valve-chatter tests were satisfactory.
Date:
December 14, 1944
Creator:
Stevens, Victor I., Jr. & McCormack, Gerald M.
Object Type:
Report
System:
The UNT Digital Library
Experimental Static Aerodynamic Forces and Moments at High Subsonic Speeds on a Canard Missile During Simulated Launching From the Midsemispan Location of a 45 Degree Sweptback Wing-Fuselage-Pylon Combination at Zero Sideslip
Report presenting an investigation at high subsonic speeds to determine the static aerodynamic forces and moments on a canard missile model during simulated launching from the midsemispan location of a 45 degree sweptback wing-fuselage-pylon combination. Significant variations in all the aerodynamic components were noted with changes in chordwise location of the missile. Results regarding force and moment characteristics and effects of angle of attack and Mach number are provided.
Date:
January 14, 1957
Creator:
Alford, William J., Jr. & King, Thomas J., Jr.
Object Type:
Report
System:
The UNT Digital Library
Preliminary Analysis of Hydrogen-Rich Hypersonic Ramjet Operation
Report discussing findings on net thrust, fuel flow, and related performance indices for hydrogen-rich operation of nacelle-type and submerged ramjet engines at various Mach numbers. Testing concluded that the system could be helpful in a flight path involving acceleration from low to high flight speeds. Some trends of the effect of the operation conditions are noted, but no conclusions are drawn because of the preliminary nature of the report.
Date:
January 14, 1958
Creator:
Breitwieser, Roland & Morris, James F.
Object Type:
Report
System:
The UNT Digital Library
An Investigation of the Longitudinal Stability Characteristics of Three Specialized Store Configurations at Transonic Speeds
Report presenting testing to determine the longitudinal stability characteristics of the TX-17, the "Short Seven", and the TX-21 special weapons. Dynamic and static stability data are provided for a range of Mach numbers and stagnation-pressure levels.
Date:
January 14, 1955
Creator:
Braden, John A.
Object Type:
Report
System:
The UNT Digital Library
Experimental and Analytical Study of Balanced-Diaphragm Fuel Distributors for Gas-Turbine Engines
"A method of distributing fuel equally to a plurality of spray nozzles in a gas-turbine engine by means of balanced-diaphragm fuel distributors is presented. The experimental performance of three of eight possible distributor arrangements are discussed. An analysis of all eight arrangements is included. Criterions are given for choosing a fuel-distributor arrangement to meet specific fuel-system requirements of fuel-distribution accuracy, spray-nozzle pressure variations, and fuel-system pressures" (p. 1).
Date:
August 14, 1950
Creator:
Straight, David M. & Gold, Harold
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic Forces and Moments on a Large Ogive-Cylinder Store at Various Locations Below the Fuselage Center Line of a Swept-Wing Bomber Configuration at a Mach Number of 1.61
"A supersonic wind-tunnel investigation on store interference has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel at a Mach number of 1.61. Forces and moments were measured on a large ogive-cylinder store in the presence of a 45 degree swept-wing-fuselage bomber configuration for a number of store locations below the fuselage center line. Results of the investigation show that large variations of store lift, drag, and pitch occur with changes in store or airplane angle of attack, store vertical location, and store horizontal location" (p. 1).
Date:
January 14, 1957
Creator:
Morris, Odell A.
Object Type:
Report
System:
The UNT Digital Library
Investigation of Afterburner Combustion Screech and Methods of Its Control at High Combustor Pressure Levels
Memorandum presenting an experimental investigation of various methods for the control of afterburner combustion screech at afterburner-inlet total pressures from 4000 to 6400 pounds per square foot absolute. Generally, the range of afterburner fuel-air ratios in which screech occurred and the intensity of screech did not vary appreciably in the range of pressures covered.
Date:
May 14, 1956
Creator:
Trout, Arthur M.; Koffel, William K. & Smolak, George R.
Object Type:
Report
System:
The UNT Digital Library
Hydrodynamic Characteristics of a Model of a Proposed Six-Engine Hull-Type Seaplane Designed for Supersonic Flight
Memorandum presenting an investigation of the hydrodynamic characteristics of a six-engine hull-type seaplane designed for supersonic flight. The configuration had four engines mounted on top of the wing in individual nacelles and two engines mounted on top of the aft section of the hull with their inlets located on top of the wing.
Date:
July 14, 1958
Creator:
Coffee, Claude W., Jr.
Object Type:
Report
System:
The UNT Digital Library
Simulated Flight Investigation of Scaled-Speed Elastic Sweptwing Bomber and Fighter Models Coupled Wing Tip to Wing Tip
Memorandum presenting a wind-tunnel investigation in which dynamic models that included elastic simulation were used to study the flight characteristics of a swept-wing bomber with parasite swept-wing fighters coupled at the wing tips. The configuration is meant to represent an efficient towing arrangement whereby the operational range of fighters can be increased.
Date:
February 14, 1956
Creator:
Thompson, Robert F.
Object Type:
Report
System:
The UNT Digital Library
Transonic Flutter Investigation of an All-Movable Horizontal Tail for a Fighter Airplane
Memorandum presenting a transonic flutter investigation of a model of an all-movable horizontal tail for a fighter airplane. The model had an aspect ratio of 3.3, a taper ratio of 0.42, and 35 degrees of sweepback of the quarter-chord line. Results regarding the analytical studies and experimental results and comparison with theory are provided.
Date:
January 14, 1957
Creator:
Land, Norman S. & Abbott, Frank T., Jr.
Object Type:
Report
System:
The UNT Digital Library
Effects of leading-edge radius and maximum thickness-chord ratio on the variation with Mach number of the aerodynamic characteristics of several thin NACA airfoil sections
Report presenting a wind-tunnel investigation to determine the effects of leading-edge radius and maximum thickness-chord ratio on the variation with Mach number of the aerodynamic characteristics of several thin symmetrical NACA 4-digit-series airfoil sections. The variations with Mach number of the lift, drag, and pitching moment for a 4-percent-chord-thick airfoil section are not significantly affected by a change of leading-edge radius from 0.18 to 0.53 percent of the chord.
Date:
April 14, 1954
Creator:
Berggren, Robert E. & Graham, Donald J.
Object Type:
Report
System:
The UNT Digital Library
Estimate of Hull-Weight Change with Varying Length-Beam Ratio for Flying Boats
"A study has been made of the variation of seaplane hull weight with length-beam ratio in a systematic series of hulls designed for constant gross weight and similar spray characteristics. It is found that increases in the length-beam ratio bring about small reductions in the hull weight if it is assumed that seaplanes having the same weight and bottom shape will be designed for the same load factor. A short discussion is also given to show the reduction in load factor that may occur with high length-beam ratios" (p. 1).
Date:
August 14, 1947
Creator:
Benscoter, Stanley U.
Object Type:
Report
System:
The UNT Digital Library
Indirect Methods for Obtaining Ram-Jet Exhaust-Gas Temperature Applied to Fuel-Metering Control
Memorandum presenting an analytical method developed that gives two independent means of obtaining the total-temperature ratio across a ram jet or across a turbojet tail-pipe burner without direct measurement of the final gas temperature. Experimental verification of the analysis has been obtained with a 20-inch ram jet over a wide range of operating conditions.
Date:
January 14, 1948
Creator:
Perchonok, Eugene; Sterbentz, William H. & Moore, Stanley H.
Object Type:
Report
System:
The UNT Digital Library
A Low-Speed Investigation of an Annular Transonic Air Inlet
Report presenting an investigation of three transonic fuselage-inlet installations designed to maintain substream velocities on the body ahead of air inlets. Surface pressures and inlet total pressures were measured at the tops of the test configurations for wide ranges of inlet-velocity ratio and angles of attack. Results indicated that substream velocities were maintained on all three noses over the angle of attack ranges and inlet-velocity ratio useful for high-speed flight.
Date:
April 14, 1947
Creator:
Nichols, Mark R. & Rinkoski, Donald W.
Object Type:
Report
System:
The UNT Digital Library
Flight Investigation of a 20-Inch-Diameter Steady-Flow Ram Jet
Memorandum presenting a flight investigation conducted on a 20-inch-diameter steady-flow ramjet at a range of altitudes and free-stream Mach numbers. Results regarding the variation of combustion efficiency with fuel-air ratio and pressure altitude, effects of combustion-chamber-inlet velocity, and altitude on the operating range of fuel-air ratio are provided. The ramjet unit operated smoothly over the entire range of velocities and altitudes with the exception of occasional rough operation at excessively rich mixtures.
Date:
January 14, 1948
Creator:
Disher, John H.
Object Type:
Report
System:
The UNT Digital Library
Experimental investigation of thrust augmentation of 4000-pound-thrust centrifugal-flow-type turbojet engine by injection of water and alcohol at compressor inlets
Report presenting an experimental investigation at zero flight speed and sea-level conditions on a 4000-pound-thrust centrifugal-flow-type turbojet engine to determine the amount of thrust augmentation obtainable at maximum rotor speed by the injection of water, alcohol, and water-alcohol mixtures at the compressor inlets. A maximum thrust augmentation of 26 percent was obtained by the injection of 4.5 pounds per second of water and 2.0 pounds per second of alcohol. Results regarding the tail-pipe gas temperature, air-flow and compressor-outlet pressure, fuel flow, specific liquid consumption, and thrust augmentation are provided.
Date:
May 14, 1948
Creator:
Jones, William L. & Engelman, Helmuth W.
Object Type:
Report
System:
The UNT Digital Library
Low-Speed Investigation of Deflectable Wing-Tip Ailerons on an Untapered 45 Degrees Sweptback Semispan Wing With and Without an End Plate
Report presenting a low-speed wind-tunnel investigation to determine the characteristics of deflectable wing-tip ailerons on an untapered 45 degree sweptback semispan wing. Ailerons with triangular and parallelogram plan forms with a maximum chord of 0.625 wing chord and a flat-plat profile were investigated. The aerodynamic characteristics in pitch and lateral control characteristics are included.
Date:
December 14, 1949
Creator:
Fischel, Jack & Watson, James M.
Object Type:
Report
System:
The UNT Digital Library
Wind-Tunnel Investigation of the Stability of Jettisoned Nose Sections of the D-558 Airplane: Phases 1 and 2
Report presenting an investigation of the stability of models of the jettisonable nose sections of D-558 airplanes in two phases. The effects of center-of-gravity location and stabilizing fins of various sizes were also determined. The noses were found to tumble end over end at an approximately horizontal axis, which may be dangerous to the pilot if the nose is jettisoned while the airplane is traveling at a high rate of speed.
Date:
January 14, 1948
Creator:
Scher, Stanley H.
Object Type:
Report
System:
The UNT Digital Library