Resource Type
Serial/Series Title
NACA Research Memorandums
141
Atomic Energy Commission Reports
53
Hanford Works Reports
22
Oak Ridge National Laboratory Reports
22
HW (Series)
17
NACA Technical Reports
17
University of California Radiation Laboratory Reports
10
ORNL (Series)
8
GJBX
6
United States Department of Energy Grand Junction Office Reports
6
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Tables of Spectral-Line Intensities: Part 2, Arranged by Wavelengths
From Abstract: "Comparisons with other intensity measurements in individual spectra indicate that the National Bureau of Standards spectral-line intensities may have average errors of 20 percent, but first of all they provide uniform quantitative values for the seventy chemical elements commonly determined by spectrochemists. These data are presented by element in part I, and all 39,000 observed lines are given in order of wavelength in part II."
Date:
October 2, 1961
Creator:
Meggers, William F.; Corliss, Charles H. & Scribner, Bourdon F.
Object Type:
Report
System:
The UNT Digital Library
Radiation Patterns in the Lower Ionosphere and Fresnel Zones for Elevated Antennas Over a Spherical Earth
From Introduction: "The purpose of this work is to give the results of a detailed computation of antenna patterns in the ionosphere at VHF over a spherical earth."
Date:
April 2, 1962
Creator:
Merrill, R. G. & Mansfield, W. V.
Object Type:
Report
System:
The UNT Digital Library
An Engineering Method for Calculating Protection Afforded by Structures Against Fallout Radiation
From Introduction: "The purpose of the paper is to discuss the assumptions and the reasoning by which the calculations described in the Engineering Manual were derived from the data in [1]. The relevant curves from [1] are given in Appendix A and the technical charts from the Engineering Manual are given in appendix B."
Date:
July 2, 1964
Creator:
Eisenhauer, Charles
Object Type:
Report
System:
The UNT Digital Library
Table of wavenumbers: Volume 1, 2000 A to 7000 A
From Extension of Tables: "Because of its range and size, this table of wavenumbers is in two volumes, Volume I presenting wavenumbers for all wavelengths between 2000 and 7000 A, and Volume II giving wave-numbers for all wavelengths from 7000 A to 10000000 A=1 mm. In some cases Volume I may suffice for ionic spectra, and in others Volume II may be adequate for molecular spectra, but in general both volumes will needed to cover the entire range of spectral wavelengths measured in standard air."
Date:
May 2, 1960
Creator:
Coleman, Charles DeWitt; Bozman, William R. & Meggers, William F.
Object Type:
Report
System:
The UNT Digital Library
High Altitude Performance Investigation of J65-B-3 Turbojet Engine With Both JP-4 and Gaseous Hydrogen Fuels
Memorandum presenting an investigation to determine the performance of the J65-B-3 turbojet engine with JP-4 and gaseous-hydrogen fuels. With JP-4 fuel, the maximum altitude for stable combustion was from about 60,000 to 65,000 feet, and the ultimate blowout limit was at an altitude of about 75,000 feet. The steady-state performance with either fuel decreased considerably with increasing altitude.
Date:
April 2, 1957
Creator:
Kaufman, Harold R.
Object Type:
Report
System:
The UNT Digital Library
Investigation of Flutter Characteristics of Three Low-Aspect-Ratio All-Movable Half-Span Control Surfaces at Mach Numbers From 1.49 to 2.87
Memorandum presenting results of a supersonic flutter investigation of three low-aspect-ratio control surfaces. Two controls were all-movable but the third had a fixed cutout. Results regarding the experiments and calculations are provided.
Date:
May 2, 1958
Creator:
Morgan, Homer G.; Figge, Irving E. & Presnell, John G., Jr.
Object Type:
Report
System:
The UNT Digital Library
Some Effects of Aeroelasticity on the Rolling Effectiveness of a 10-Percent-Scale Model of the Mcdonnell F-101A Airplane Wing at Mach Numbers From 0.5 to 1.2
Report discussing testing of the effects of aeroelasticity on the rolling effectiveness on a model of a McDonnell F-101A airplane wing. The aeroelastic losses varied based on the Mach number and altitude.
Date:
September 2, 1955
Creator:
English, Roland D.
Object Type:
Report
System:
The UNT Digital Library
Effects of Modifications to a Control Surface on a 6-Percent-Thick Unswept Wing on the Transonic Control-Surface Flutter Derivatives
Transonic flutter derivatives for unswept wing control surface configurations determined by pressure cell measurements. The control surfaces were mounted on a wing with an aspect ratio of 3, a taper ratio of 0.6, and a wing-thickness ratio of 0.06. Results regarding aerodynamic balance, vortex generators, splitter-plate configurations, and wedges are provided.
Date:
May 2, 1958
Creator:
Wyss, John A.; Sorenson, Robert M. & Gambucci, Bruno J.
Object Type:
Report
System:
The UNT Digital Library
NACA Investigations of Icing-Protection Systems for Turbojet-Engine Installations
"Investigations have been made in flight and in wind tunnels to determine which components of turbojet installations are most critical in icing conditions, and to evaluate several methods of icing protection. From these studies, the requirements necessary for adequate icing protection and the consequent penalties on engine performance can be estimated. Because investigations have indicated that the compressor-inlet screen constitutes the greatest icing hazard and is difficult to protect, complete removal or retraction of the screen upon encountering an icing condition is recommended" (p. 1).
Date:
May 2, 1951
Creator:
von Glahn, Uwe; Callaghan, Edmund E. & Gray, Vernon H.
Object Type:
Report
System:
The UNT Digital Library
General Theory of Aerodynamic Instability and the Mechanism of Flutter
"The aerodynamic forces on an oscillating airfoil or airfoil-aileron combination of three independent degrees of freedom were determined. The problem resolves itself into the solution of certain definite integrals, which were identified as Bessel functions of the first and second kind, and of zero and first order. The theory, based on potential flow and the Kutta condition, is fundamentally equivalent to the conventional wing section theory relating to the steady case" (p. 291).
Date:
May 2, 1934
Creator:
Theodorsen, Theodore
Object Type:
Report
System:
The UNT Digital Library
Large-Scale Wind-Tunnel Tests of an Airplane Model With a 45 Degree Sweptback Wing of Aspect Ratio 2.8 With Area Suction Applied to Trailing-Edge Flaps and With Several Wing Leading-Edge Modifications
Memorandum presenting an investigation of an airplane model to determine the effect of area suction trailing-edge flaps and several leading-edge modifications on the aerodynamic characteristics of a 45 degree sweptback wing. The wing had an aspect ratio of 2.8 and a taper ratio of 0.17.
Date:
November 2, 1956
Creator:
Koenig, David G. & Aoyagi, Kiyoshi
Object Type:
Report
System:
The UNT Digital Library
Tests With Hydrogen Fuel in a Simulated Afterburner
Report presenting an investigation in a 16-inch-diameter simulated afterburner using gaseous hydrogen fuel. Results regarding combustion efficiency, afterburner pressure losses, spontaneous ignition, and a heat-balance check are provided.
Date:
July 2, 1956
Creator:
Kerslake, W. R. & Dangle, E. E.
Object Type:
Report
System:
The UNT Digital Library
Organophosphorus Compounds in Rocket-Engine Applications
Report discussing the ignition-delay determinations of three organophosphorous fuels with nitric acid oxidants at simulated altitude conditions with a small-scale rocket engine.
Date:
April 2, 1954
Creator:
Ladanyi, Dezso J. & Hennings, Glen
Object Type:
Report
System:
The UNT Digital Library
Some Research on the Lift and Stability of Wing-Body Combinations
The present paper summarizes and correlates broadly some of the research results applicable to fin-stabilized ammunition. The discussion and correlation are intended to be comprehensive, rather than detailed, in order to show general trends over the Mach number range up to 7.0. Some discussion of wings, bodies, and wing-body interference is presented, and a list of 179 papers containing further information is included. The present paper is intended to serve more as a bibliography and source of reference material than as a direct source of design information.
Date:
July 2, 1959
Creator:
Purser, Paul E. & Fields, E. M.
Object Type:
Report
System:
The UNT Digital Library
Performance of a Short Turbojet Combustor With Hydrogen Fuel in a Quarter-Annulus Duct and Comparison With Performance in a Full-Scale Engine
Memorandum presenting an investigation of a number of short turbojet combustor configurations for hydrogen fuel in a quarter-annulus duct. The best combustor liner consisted of an annular primary zone and a secondary zone composed of T-shaped channels sloping from the primary zone to the combustor wall.
Date:
July 2, 1956
Creator:
Friedman, Robert; Norgren, Carl T. & Jones, Robert E.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic Characteristics of Low-aspect-ratio Wings at High Supersonic Mach Numbers
Memorandum presenting some recently obtained data on the aerodynamic characteristics of low-aspect-ratio wings at supersonic Mach number of 4.04 and 6.9 and discusses some new methods of predicting the lift and drag of such wings. The plan forms, airfoil sections, and thickness ratios of the wings tested are provided.
Date:
November 2, 1953
Creator:
Ulmann, Edward F. & Bertram, Mitchel H.
Object Type:
Report
System:
The UNT Digital Library
Characteristics of a 15-Percent-Chord and a 35-Percent-Chord Plain Flap on the NACA 0006 Airfoil Section at High Subsonic Speeds
Memorandum presenting wind-tunnel tests to determine the aerodynamic characteristics of a 15-percent- and a 35-percent-chord plain trailing-edge flap on the NACA 0006 airfoil section. Simultaneous measurements of section lift, drag, and pitching moment were made over a range of Mach numbers, angles of attack, and flap deflections.
Date:
October 2, 1947
Creator:
Ilk, Richard J.
Object Type:
Report
System:
The UNT Digital Library
Preliminary Analysis of Problem of Determining Experimental Performance of Air-Cooled Turbine 3: Methods for Determining Power and Efficiency
Suggested formula are given for determining air-cooled turbine-performance characteristics, such as power and efficiency, as functions of certain parameters. These functions, generally being unknown, are determined from experimental data obtained from specific investigations. Special plotting methods for isolating the effect of each parameter are outlined.
Date:
August 2, 1950
Creator:
Ellerbrock, Herman H., Jr. & Ziemer, Robert R.
Object Type:
Report
System:
The UNT Digital Library
Lateral-control investigation of flap-type controls on a wing with quarter-chord line swept back 60 degrees, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section: transonic bump method
Report presenting an investigation by the transonic-bump method through a range of Mach numbers in the high-speed 7- by 10-foot tunnel to determine the lateral-control characteristics of 30-percent-chord flap-type controls of various spans and locations. The wing of the semispan fuselage-wing combination had 60 degrees of sweepback of the quarter-chord line, a taper ratio of 0.6, an aspect ratio of 4.0, and an NACA 65A006 airfoil section parallel to the free air stream.
Date:
March 2, 1950
Creator:
Vogler, Raymond D.
Object Type:
Report
System:
The UNT Digital Library
Preliminary analysis of effects of air cooling turbine blades on turbojet-engine performance
The effects of turbine-blade cooling on engine performance were analytically investigated for a turbojet engine in which cooling air is bled from the engine compressor. The analysis was made for a constant turbine-inlet temperature and a range of altitudes to determine the minimum cooling requirements to permit substitution of nonstrategic materials in turbine blading. The results indicate that, for a constant inlet temperature, air cooling of the turbine blades increases the specific fuel consumption and decreases the thrust of the engine. The highest possible cooling effectiveness is desirable to minimize coolant weight flow and its effects on engine performance.
Date:
August 2, 1950
Creator:
Schramm, Wilson B.; Nachtigall, Alfred J. & Arne, Vernon L.
Object Type:
Report
System:
The UNT Digital Library
Free-Fall Measurements at Transonic Velocities of the Drag of a Wing-Body Configuration Consisting of a 45 Degree Swept-Back Wing Mounted Forward of the Maximum Diameter on a Body of Fineness Ratio 12
Report presenting the drag of a series of complete airplane-like configurations and their components at transonic velocities using the free-fall method. The configuration tested in this report has a 45 degree sweptback wing of aspect ratio 4.1 mounted forward of the maximum diameter of a 10-inch-diameter body of fineness ratio 12 equipped with stabilizing tail fins. Results are presented as curves showing the variation of drag coefficient with Mach number for the complete configuration and for each component.
Date:
April 2, 1947
Creator:
Mathews, Charles W. & Thompson, Jim Rogers
Object Type:
Report
System:
The UNT Digital Library
Comparison of performance of AN-F-58 and AN-F-32 fuels in J33-A-23 turbojet engine
Report presenting an investigation using a 4600 pound-thrust turbojet engine as part of a program to determine the comparative performance of fuels conforming to specifications AN-F-58 and AN-F-32. Results regarding the altitude performance, altitude low-speed blow-out limits, idling limits of fuel-metering control, altitude windmilling starts, carbon-deposition rates, and iron oxide contamination are provided.
Date:
June 2, 1949
Creator:
Wilsted, H. D. & Armstrong, J. C.
Object Type:
Report
System:
The UNT Digital Library
An Approximate Method for Estimating the Incompressible Laminar Boundary-Layer Characteristics on a Flat Plate in Slipping Flow
Memorandum presenting an approximate method for the estimation of the properties of the incompressible laminar boundary layer on a flat plate in the slip-flow region using Karman's momentum method. At equivalent stations, the total thickness and the skin friction of a slipping boundary layer are less than that of the normal boundary layer at the same Reynolds number.
Date:
May 2, 1949
Creator:
Donaldson, Coleman duP.
Object Type:
Report
System:
The UNT Digital Library
Flight Investigation of the Jettisonable-Nose Method of Pilot Escape Using Rocket-Propelled Models
Report discussing testing using two rocket-propelled models to test the jettisonable-nose method of pilot escape. The nose was jettisoned successfully on the second attempt and the accelerations produced were found to be within human tolerance. The first test ended with a collision of the nose and wing, indicating that this is a possible risk during power-on flight.
Date:
June 2, 1949
Creator:
Lundstrom, Reginald R. & O'Kelly, Burke R.
Object Type:
Report
System:
The UNT Digital Library