Resource Type
Serial/Series Title
NACA Research Memorandums
173
Atomic Energy Commission Reports
61
NACA Technical Reports
30
Hanford Works Reports
20
HW (Series)
16
Oak Ridge National Laboratory Reports
15
University of California Radiation Laboratory Reports
12
AEC research and development report
6
AECU (Series)
6
BNL (Series)
6
55 More
Country
States
Decade
Month
Day
331 Matching Results
Results open in a new window/tab.
Theoretical Investigation of Laminar Heat Transfer on Yawed Infinite Cylinders in Supersonic Flow and a Comparison With Experimental Data
Report presenting a theoretical method for calculating heat transfer in the laminar boundary layer on yawed infinite cylinders in compressible flow. The method can be applied to a cylinder of arbitrary cross section and arbitrary chordwise wall-temperature distribution. The variation in local heat transfer around the surface of the cylinder was found to have little functional dependence on yaw angle or wall temperature.
Date:
August 9, 1955
Creator:
Beckwith, Ivan E.
Object Type:
Report
System:
The UNT Digital Library
Tests of Aerodynamically Heated Multiweb Wing Structures in a Free Jet at Mach Number 2: Two Aluminum-Alloy Models of 20-Inch Chord With 0.064- and 0.081-Inch-Thick Skin
Report presenting testing of two 2024-T3 aluminum-alloy multiweb wing structures (MW-2 and MW-3), similar to airplane or missile wings, at a Mach number of 2 under simulated supersonic flight conditions. Results regarding experimentally determined test conditions, model temperatures, strain-gage results, and model failures are provided. The report indicates that much of the stress data does not agree with expected results, but there is too much uncertainty regarding the reduction of strain data that no conclusions can be made concerning the results.
Date:
August 9, 1955
Creator:
Griffith, George E.; Miltonberger, Georgene H. & Rosecrans, Richard
Object Type:
Report
System:
The UNT Digital Library
Analysis of Low-Temperature Nuclear-Powered Ram-Jet Missile for High Altitudes
Report presenting the gross weight and uranium investment of nuclear-powered, direct-air, shieldless, ram-jet missiles for a range of altitudes and Mach numbers. Results regarding the effect of reactor operating conditions and flight conditions on ramjet performance and effect of assumptions on ramjet performance are provided.
Date:
November 9, 1955
Creator:
Sams, Eldon W. & Rom, Frank E.
Object Type:
Report
System:
The UNT Digital Library
Aircraft-Fuel-Tank Design for Liquid Hydrogen
"Some of the considerations involved in the design of aircraft fuel tanks for liquid hydrogen are discussed herein. Several of the physical properties of metals and thermal insulators in the temperature range from ambient to liquid-hydrogen temperatures are assembled. Calculations based on these properties indicate that it is possible to build a large-size liquid-hydrogen fuel tank which (1) will weigh less then 15 percent of the fuel weight, (2) will have a hydrogen vaporization rate less than 30 percent of the cruise fuel-flow rate, and (3) can be held in a stand-by condition and readied for flight in a short time" (p. 1).
Date:
August 9, 1955
Creator:
Reynolds, T. W.
Object Type:
Report
System:
The UNT Digital Library
An Investigation of the Mutual Interference Effects of a Tail-Surface: Stern Propeller Installation on a Model Simulating the Douglas XB-42 Empennage
Report discussing the mutual interference effects of tail surfaces and a stern propeller on a model of the XB-42.The main focus was to determine the effect of tail surface-propeller spacing upon the periodic tail surface loading coincident with propeller blade passage.
Date:
November 9, 1944
Creator:
Bartlett, Walter A., Jr. & Marino, Alfred A.
Object Type:
Report
System:
The UNT Digital Library
High-Altitude Performance of an Experimental Turbular Prevaporizing Combustor
Memorandum presenting an investigation of an experimental tubular combustor that provides for prevaporizing and premixing of the fuel with a part of the air before its introduction into the combustion zone. Combustion efficiency and total-pressure loss data are presented for three configurations selected from a total of 43 different modifications investigated. Results regarding the combustor development, comparison of liquid and gaseous fuel, combustor total-pressure losses, combustor-outlet temperature distribution, and evaluation of experimental prevaporizing combustors are provided.
Date:
December 9, 1954
Creator:
Butze, Helmut F.
Object Type:
Report
System:
The UNT Digital Library
Comparative drag measurements at transonic speeds of rectangular sweptback NACA 65-009 airfoils mounted on a freely falling body
From Summary: "Directly comparable drag measurements have been made of an airfoil with a conventional rectangular plan form and an airfoil with a sweptback plan form mounted on freely falling bodies. Both airfoils had NACA 65-009 sections and were identical in span, frontal area, and chord perpendicular to the leading edge. The sweptback plan form incorporated a sweepback angle of 45 degrees. The data obtained have been used to establish the relation between the airfoil drag coefficients and the free-stream Mach number over a range of Mach numbers from 0.90 to 1.27. The results of the measurements indicate that the drag of the sweptback plan form is less than 0.3 that of the rectangular plan form at a Mach number of 1.00 and is less than 0.4 that at a Mach number of 1.20."
Date:
August 9, 1945
Creator:
Mathews, Charles W. & Thompson, Jim Rogers
Object Type:
Report
System:
The UNT Digital Library
Analysis of rocket, ram-jet, and turbojet engines for supersonic propulsion of long-range missiles 1: rocket-engine performance
Report presenting theoretical performance characteristics and estimates of effective specific impulse and weight for rocket engines serving a main and booster power plants for missiles. The fuels used included ammonia-fluorine and JP4-oxygen propellants. At extremely high altitudes, the specific impulse depends primarily on the expansion ratio.
Date:
July 9, 1954
Creator:
Huff, Vearl N. & Kerrebrock, Jack
Object Type:
Report
System:
The UNT Digital Library
Stability and Control Characteristics at Low Speed of a Modified 1/10-Scale Model of the MX-1554A Design
Report discussing the low-speed stability and control characteristics of a modified model of the MX-1554A with a triangular wing and triangular stabilizing surfaces, which are designed to give more satisfactory stability and control than previous versions. Other modifications included an increase in slotted-flap span, redesigned tip aileron, fuselage tail cone, and speed brakes. Results provided include the effect of flow-control devices, tank and pylon location, a ground board, rotary stability derivatives, and a single support strut on the stability, control, and aerodynamic characteristics.
Date:
November 9, 1953
Creator:
Lockwood, Vernard E. & Solomon, Martin
Object Type:
Report
System:
The UNT Digital Library
Nonuniform Burnup and Poisoning Effects in a Reactor and Validity of Uniform Approximation
Memorandum presenting the application of the nuclear-reactor simulator to an investigation of the validity of the customary assumption of uniform distributions of fuel burnup and fission-product poisoning in a reactor core. The two-group calculation results show the effects of the approximation on the reactivity, power distribution, and xenon-135 distribution for a specific power reactor in which the initial power density varied by a factor of approximately 4 over the core volume.
Date:
March 9, 1953
Creator:
Spooner, Robert B.
Object Type:
Report
System:
The UNT Digital Library
Full-Scale Wind-Tunnel Tests of a North American FJ-3 Airplane with a Spoiler-Slot-Deflector Lateral Control System
Report discussing an investigation to determine the low-speed aerodynamic characteristics of a North American FJ-3 airplane with a segmented spoiler-slot-deflector lateral control system installed ahead of convention ailerons and operated as individual units and as combined segments. The longitudinal characteristics of the plane, the spoiler-slot-deflector effectiveness, and spoiler-deflector hinge-moment data are all described.
Date:
April 9, 1956
Creator:
Scallion, William I.
Object Type:
Report
System:
The UNT Digital Library
Analytical Studies of the Response to Longitudinal Control of Three Airplane Configurations in Landing Approaches
Memorandum presenting a theoretical investigation to determine the reasons for poor airplane response to longitudinal control. Some effects of airplane configuration on the response, primarily for short time periods, were also determined. Results regarding a comparison of three airplanes, the effect of changes on airplane B, and the effect of changes on airplane C are provided.
Date:
April 9, 1953
Creator:
Bihrle, William, Jr. & Stone, Ralph W., Jr.
Object Type:
Report
System:
The UNT Digital Library
Effect of diffuser design, diffuser-exit velocity profile and fuel distribution on altitude performance of several afterburner configurations
"An investigation was conducted in the NACA Lewis altitude wind tunnel to improve the altitude performance and operational characteristics of an afterburner primarily by modifying the diffuser-exit velocity profile by changes in diffuser design and by changing the fuel distribution and the flame holder. Twenty configurations, consisting of combinations of six diffuser geometries, six flame-holder types, and twelve fuel systems, were investigated. Data were obtained over a range of afterburner fuel-air ratios at diffuser-inlet total pressures from 2750 to 620 pounds per square foot" (p. 1).
Date:
July 9, 1953
Creator:
Conrad, E. William; Schultz, Frederick W. & Usow, Karl H.
Object Type:
Report
System:
The UNT Digital Library
Correlation Between Hydrogen Pressure and Protective Action of Additives in the Molten Sodium Hydroxide - Nickel System
Memorandum presenting an investigation of the effect of various metallic additives on the molten sodium hydroxide - nickel system. The hydrogen evolved from such systems was measured and the evolution was correlated with the effect of the metal on mass transfer. Results regarding a check with standard tests, purging, presence of two valences for chromium, reaction time of the additive, and pressure within nickel crucibles are provided.
Date:
February 9, 1956
Creator:
May, Charles E.
Object Type:
Report
System:
The UNT Digital Library
Effectiveness of Inhibitors for Mass Transfer and Corrosion in Sodium Hydroxide - Nickel Systems
Memorandum presenting static crucible tests with additions of the reducing agents sodium chromite Na(sub 3)CrO(sub 4) and manganese dioxide MnO(sub 2) indicate that salts soluble in sodium hydroxide may be added to inhibit mass transfer in nickel. The metals manganese, vanadium, and molybdenum were also investigated in static crucibles and found to be ineffective.
Date:
February 9, 1956
Creator:
Forestieri, Americo F. & Lad, Robert A.
Object Type:
Report
System:
The UNT Digital Library
Free Spinning and Recovery Characteristics of 1/36-Scale Model of the Republic F-105B Airplane
Report presenting an investigation in the free-spinning tunnel on a model of the Republic F-105B airplane to determine the spin and recovery characteristics. Results indicated that even with perfect control technique, full movement of the rudder against the spin and of ailerons with the spin is not adequate to ensure satisfactory recovery; extensions of both canard surfaces should accompany the control technique. Results regarding ideal parachute design are also provided.
Date:
October 9, 1957
Creator:
Bowman, James S., Jr.
Object Type:
Report
System:
The UNT Digital Library
An Electric Thrust Meter Suitable for Flight Investigation of Propellers
A lightweight instrument that utilizes resistance-wire electric strain gases to measure propeller-shaft thrust has been developed. A wind-tunnel investigation on a propeller installed, on a single-engine pursuit airplane showed that the instrument gave a reliable indication of propeller-shaft thrust to an accuracy of +/-2 percent within its calibrated range. No attempt was made to determine the relation of indicated shaft thrust to net propeller thrust.
Date:
May 9, 1949
Creator:
Perkins, Porter J., Jr. & Millenson, Morton B.
Object Type:
Report
System:
The UNT Digital Library
Analysis of Low-Temperature Nuclear-Powered Ramjet Missile for High Altitudes
From Summary: "The reactor operating conditions were varied to enable selection of values giving a good compromise between low uranium investment and loss gross weight at each altitude and flight Mach number considered. The corresponding values of reactor and missile operating conditions are presented in the report."
Date:
November 9, 1955
Creator:
Rom, F. E. & Sams, E. W.
Object Type:
Report
System:
The UNT Digital Library
Investigations of Air-Cooled Turbine Rotors for Turbojet Engines 1: Experimental Disk Temperature Distribution in Modified J33 Split-Disk Rotor at Speeds up to 6000 RPM
"An experimental investigation is being conducted at the Lewis laboratory to establish general principles for the design of noncritical turbine rotor configurations. This investigation includes evaluation of cooling effectiveness, structural stability, cooling-air flow distribution characteristics, and methods of supplying cooling air to the turbine rotor blades. Prior to design of a noncritical rotor, a standard turbine rotor of a commerical turbojet engine was split in the plane of rotation and machined to provide a passage for distributing cooling air to the base of each blade" (p. 1).
Date:
January 9, 1952
Creator:
Schramm, Wilson B. & Ziemer, Robert R.
Object Type:
Report
System:
The UNT Digital Library
Hovering and Transition Flight Tests of a 1/5-Scale Model of the Ryan X-13 VTOL Airplane
Report discussing an investigation of the dynamic stability and control characteristics of a model of the Ryan X-13 jet VTOL airplane in hovering and transition flight. Flight control was smooth and easy without the gyroscopic effects of the engine represented, but adding a simulation of the gyroscopic effects caused the plane to become uncontrollable in hovering flight without artificial stabilization. The transition was found to be easy to perform with and without gyroscopic effects, but the model had a tendency to fly in roll and slideslipped attitudes.
Date:
September 9, 1958
Creator:
Smith, Charles C., Jr.
Object Type:
Report
System:
The UNT Digital Library
Preliminary Investigation of Reflections of Oblique Waves from a Porous Wall
"A porous wall was used in an attempt to eliminate reflections of oblique waves from a tunnel wall. Calculations were made of the required resistance characteristics of a wall in order that the flow through the wall, due to the pressure difference across a shock wave, would equal the component normal to the wall of the flow behind the shock wave. The resistance characteristic of a sintered bronze wall was measured and the reflections of waves impinging on the wall were observed at a Mach number of 1.62" (p. 1).
Date:
November 9, 1950
Creator:
Davis, Don D., Jr. & Wood, George P.
Object Type:
Report
System:
The UNT Digital Library
Supplementary Free-Spinning-Tunnel Investigation of a 1/20-Scale Model of the McDonnell F2H-3 Airplane With External Stores Installed
Memorandum presenting a supplementary investigation in the 20-foot free-spinning tunnel to determine the effect of external stores and lateral center-of-gravity displacement on the spin and spin-recovery characteristics of a scale model of the McDonnell F2H-3 airplane. Results regarding wing-tip tanks and experimental aerodynamic shapes are provided.
Date:
June 9, 1952
Creator:
Wilson, Jack H.
Object Type:
Report
System:
The UNT Digital Library
Low-Pressure Performance of a Tubular Combustor With Gaseous Hydrogen
Memorandum presenting an investigation to determine the combustion performance characteristics of gaseous hydrogen fuel in a single tubular turbojet combustor. The combustor was operated over a range of inlet-air pressures from 3.3 to 14.3 inches of mercury absolute. Results regarding stability limits and combustion efficiency are provided.
Date:
May 9, 1955
Creator:
Jonash, Edmund R.; Smith, Arthur L. & Hlavin, Vincent F.
Object Type:
Report
System:
The UNT Digital Library
Tests of the Landing on Water of a Model of a High-Speed Airplane - Langley Tank Model 229
Memorandum presenting an investigation at the tank no. 2 monorail of the landing on smooth water of a scale model of a hypothetical jet- and rocket-propelled airplane designed to fly at transonic speeds. The test is part of an investigation of the feasibility of the operation from water of high-speed airplanes. The results of the test form a basis for evaluating the improvement in hydrodynamic characteristics.
Date:
December 9, 1947
Creator:
King, Douglas A.
Object Type:
Report
System:
The UNT Digital Library