Resource Type
Serial/Series Title
Atomic Energy Commission Reports
155
NACA Research Memorandums
143
AEC research and development report
33
GJBX
31
Hanford Works Reports
30
HW (Series)
25
University of California Radiation Laboratory Reports
25
NACA Technical Reports
23
Report (U.S. Atomic Energy Commission)
21
United States Department of Energy Grand Junction Office Reports
20
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Preservation of Documents by Lamination
From Abstract: "Composition and performance specifications for a cellulose acetate laminating film suitable for a cellulose acetate laminating film suitable for archival use are presented. The properties of polyethylene and polyethylene terephthalate films of interest in connection with their possible use for the protection of documents are discussed."
Date:
October 30, 1959
Creator:
Wilson, William K. & Forshee, B. W.
Object Type:
Report
System:
The UNT Digital Library
Electrical Parameters of Precision, Coaxial, Air-dielectric Transmission Lines
From Introduction: "Following the guidelines established by this committee, several commercially developed precision connectors have appeared on the market which have led to the wide use of the precision coaxial lines as immittance standards. This paper has been prepared to alleviate this situation by providing graphs from which the electrical parameters of the lines may be determined rapidly and accurately."
Date:
June 30, 1966
Creator:
Nelson, Robert E. & Coryell, Marlene R.
Object Type:
Report
System:
The UNT Digital Library
Sound Insulation of Wall, Floor, and Door Constructions
From Abstract: "The data obtained at the National Bureau of Standards on the sound insulating properties of building structures are summarized. A brief description of the sound-measuring techniques is given."
Date:
November 30, 1964
Creator:
Berendt, Raymond D. & Winzer, George E.
Object Type:
Report
System:
The UNT Digital Library
Health and Safety Laboratory Fallout Program Quarterly Summary Report: September 1, 1961 - December 1, 1961
Report that summarizes multiple laboratories' reports on global fallout deposition. Reports include data on Strontium-90 deposition recorded by the Health and Safety Laboratory, data from other laboratories, related interpretive reports, and recent publications related to fallout.
Date:
December 30, 1961
Creator:
Hardy, Edward P., Jr.; Rivera, Joseph & Frankel, Robert
Object Type:
Report
System:
The UNT Digital Library
Wing Pressure Distributions Over the Lift Range of the Convair XF-92A Delta-Wing Airplane at Subsonic and Transonic Speeds
Report presenting chordwise pressure distributions measured over the left wing of the Convair XF-92A delta-wing airplane to determine the effect of lift on the wing characteristics at subsonic and transonic Mach numbers. Results regarding the chordwise pressure distributions, wing-section aerodynamic characteristics, spanwise distribution, and elevon-section loads are provided.
Date:
November 30, 1955
Creator:
Keener, Earl R. & Jordan, Gareth H.
Object Type:
Report
System:
The UNT Digital Library
Investigation of Drag and Static Longitudinal and Lateral Stability Characteristics of a 1/15-Scale Model of the Grumman F11F-1F Airplane at Mach Numbers of 1.56, 1.76, 2.06, and 2.53
Report presenting an investigation in the Langley Unitary Plan wind tunnel to determine the drag and static longitudinal and lateral stability characteristics of a model of the Grumman F11F-1F airplane at Mach numbers 1.56, 1.76, 2.06, and 2.53. The investigation included the effects on performance and stability of modifications, including a wing-root leading-edge fillet and horizontal tails with negative dihedral of 10 degrees and 30 degrees. Information regarding net external minimum drag coefficients, neutral points, directional stability, and positive effective dihedral is provided.
Date:
November 30, 1956
Creator:
Turner, Kenneth L. & Fournier, Roger H.
Object Type:
Report
System:
The UNT Digital Library
A Wind-Tunnel Investigation of the Effects of Conical Camber for an Airplane Configuration Having a Triangular Wing of Aspect Ratio 2.2
Memorandum presenting the results of an investigation directed at determining the effectiveness of various amounts and spanwise extents of conical camber on the aerodynamic characteristics of a wing-body-tail combination employing a triangular wing of aspect ratio 2.2. Five cambered wings were tested, all of which were designed for a Mach number of 1.0. Results regarding drag characteristics and lift and moment characteristics are provided.
Date:
April 30, 1957
Creator:
Phelps, E. Ray & Boyd, John W.
Object Type:
Report
System:
The UNT Digital Library
Wind-Tunnel Investigation at High Subsonic Speeds of the Effects on Static Stability Characteristics of Various Modifications to a Swept-Wing Fighter-Type Airplane Model
Memorandum presenting an investigation at high subsonic speeds of a model of a twin-engine swept-wing fighter-type airplane. The model was tested with several different tail configurations and with several wing and engine inlet modifications. Results regarding pitching-moment characteristics, lift and drag characteristics, and lateral derivatives are provided.
Date:
April 30, 1957
Creator:
Goodson, Kenneth W.
Object Type:
Report
System:
The UNT Digital Library
Experimental Investigation at High Subsonic Speeds of the Rolling-Stability Derivatives of a 1/22 Scale Model of the Republic F-105 Airplane
Report presenting an investigation of the rolling-stability derivatives for a model of the Republic F-105 airplane over a range of Mach numbers and angles of attack. The model retained damping in roll through the test ranges, but values of the damping varied considerably with angles of attack. Derivatives of yawing moment and lateral force due to rolling generally followed previously indicated trends.
Date:
June 30, 1955
Creator:
Sleeman, William C., Jr. & Hayes, William C., Jr.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic Characteristics of a 0.04956-Scale Model of the Convair F-102A Airplane at Mach Numbers of 1.41, 1.61, and 2.01
"Tests have been made in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.41, 1.61, and 2.01 of various arrangements of a 0.04956-scale model of the Convair F-102A airplane with faired inlets. Tests made of the model equipped with a plain wing, a wing with 6.4 percent conical camber, and a wing with 15 percent conical camber. Body modifications including an extended nose, a modified canopy, and extended afterbody fillets were evaluated" (p. 1).
Date:
September 30, 1955
Creator:
Spearman, M. Leroy & Driver, Cornelius
Object Type:
Report
System:
The UNT Digital Library
Investigation of the Static Stability Characteristics of Five Hypersonic Missile Configurations at Mach Numbers From 2.29 to 4.65
Report presenting an investigation to determine the static stability characteristics of five hypersonic missile configurations. Testing was performed at a range of Mach and Reynolds numbers. Results regarding the effect of base block, longitudinal stability, directional stability, and Reynolds number effect are provided.
Date:
June 30, 1958
Creator:
Turner, Kenneth L. & Appich, W. H., Jr.
Object Type:
Report
System:
The UNT Digital Library
Flight Investigation at Low Angles of Attack to Determine the Longitudinal Stability and Control Characteristics of a Cruciform Canard Missile Configuration With a Low-Aspect-Ratio Wing and Blunt Nose at Mach Numbers From 1.2 to 2.1
Report presenting flight testing of a rocket-powered model of a cruciform canard missile configuration with a low-aspect-ratio wing and blunt nose. Results regarding the lift coefficient, dynamic stability, static stability, control effectiveness, and drag are provided.
Date:
September 30, 1957
Creator:
Brown, Clarence A., Jr.
Object Type:
Report
System:
The UNT Digital Library
Experimental Investigation of Air-Cooled Turbine Blades in Turbojet Engine: 1: Rotor Blades With 10 Tubes in Cooling-Air Passages
Report presenting an investigation to experimentally determine the effectiveness of air cooling several turbine-blade configurations in a turbojet engine. The results obtained with the first configuration, which was a hollow blade shell with 10 tube inserts, are presented. A description of factors leading to the design are provided as well as the correlated cooled-blade temperatures, solid-blade temperatures, cooling-air-temperature increase through radial passages, and blade failure are provided.
Date:
July 30, 1950
Creator:
Ellerbrock, Herman H., Jr. & Stepka, Francis S.
Object Type:
Report
System:
The UNT Digital Library
Preliminary Performance Data Obtained in a Full-Scale Free-Jet Investigation of a Side-Inlet Supersonic Diffuser
Report discussing an investigation into the performance of several modifications of a side-inlet ramjet engine diffuser. Total-pressure-recovery profiles, Mach number profiles, longitudinal wall static pressure distributions, and variation of the average-static to average-total pressure are presented.
Date:
November 30, 1954
Creator:
Farley, John M. & Smith, Ivan D.
Object Type:
Report
System:
The UNT Digital Library
Analysis of Heat Transfer and Fluid Friction for Fully Developed Turbulent Flow of Supercritical Water With Variable Fluid Properties in a Smooth Tube
From Summary: "Calculated velocity and temperature distributions, as well as relations among Nusselt number, Reynolds number, and friction factor, are presented."
Date:
January 30, 1953
Creator:
Deissler, R. G. & Taylor, M. F.
Object Type:
Report
System:
The UNT Digital Library
Experimental and Theoretical Determination of Forces and Moments on a Store and on a Store- Pylon Combination Mounted on a 45 Degree Swept- Wing-Fuselage Configuration at a Mach Number of 1.61
Forces and moments of store-pylon combination mounting on swept wing-fuselage configuration in supersonic pressure tunnel. The results of the investigation indicate that the most important source of store-pylon side forces is the pylon itself.
Date:
January 30, 1958
Creator:
Morris, Odell A.; Carlson, Harry W. & Geier, Douglas J.
Object Type:
Report
System:
The UNT Digital Library
Performance of an Inlet Having a Variable-angle Two-dimensional Compression Surface and a Fixed-geometry Subsonic Diffuser for Application to Reduced Engine Rotative Speeds- Mach Numbers 0.66, 1.5, 1.7, and 2.0
Report presenting the performance of a two-dimensional side inlet with a technique of varying compression-surface angle while retaining a fixed-geometry diffuser at several Mach numbers and zero angle of attack. A 12 degree compression ramp was faired into the diffuser contour in this conventional manner. Results regarding the inlet flow field, application to reduced engine speeds, and a inlet performance with a sudden expansion in the diffuser are provided.
Date:
January 30, 1958
Creator:
Allen, John L.
Object Type:
Report
System:
The UNT Digital Library
Low-Temperature Chemical Starting of a 200-Pound-Thrust JP-4 - Nitric Acid Rocket Engine Using a Three-Fluid Propellant Valve
Low-temperature chemical starting of combined JP-4 nitric acid propellant for low-thrust rocket engine using three-fluid propellant valve.
Date:
June 30, 1955
Creator:
Hennings, Glen & Morrell, Gerald
Object Type:
Report
System:
The UNT Digital Library
Use of Highly Reactive Chemical Additives to Improve Afterburner Performance at Altitude
Memorandum presenting an investigation in an altitude test chamber to evaluate the use of highly reactive chemicals injected into a turbojet afterburner to promote the combustion process, which was inhibited by water vapor from compressor-inlet injection. The chemicals evaluated were commercial hydrogen and aluminum trimethyl. Results regarding the effects of hydrogen injection on afterburner performance and effect of aluminum trimethyl afterburner fuel additive on performance are provided.
Date:
September 30, 1958
Creator:
Wanhainen, John P. & Sivo, Joseph N.
Object Type:
Report
System:
The UNT Digital Library
Tabulated Pressure Data for a Series of Controls on a 60 Degree Delta Wing at Mach Numbers of 1.61 and 2.01
"An investigation has been made at Mach numbers of 1.61 and 2.01 and Reynolds numbers from 1.7 x 10(exp 6) to 7.6 x 10(exp 6) to determine the pressure distributions over a 60 degree delta wing having 20 different control configurations. Measurements were made at angles of attack from 0 to 15 degrees for control deflections from -30 to 30 degrees. This report presents the complete tabulated pressure data for the range of test conditions" (p. 1).
Date:
March 30, 1956
Creator:
Lord, Douglas R. & Czarnecki, K. R.
Object Type:
Report
System:
The UNT Digital Library
Off-Design Performance of Divergent Ejectors
Report presenting an investigation of the off-design performance of fixed- and variable-geometry divergent ejectors. Results regarding fixed geometry and low secondary flow, fixed geometry and high secondary flow, variable geometry and low secondary flow, variable geometry and high secondary flow, and ejectors with full afterburning are provided.
Date:
September 30, 1958
Creator:
Beheim, Milton A.
Object Type:
Report
System:
The UNT Digital Library
Performance of a Single Fuel-Vaporizing Combustor With Six Injectors Adapted for Gaseous Hydrogen
Report presenting an investigation in a single tubular combustor to determine the effectiveness of hydrogen fuel using an annular fuel-vaporizing combustor in a full-scale turbojet engine. Six different fuel-injector designs were investigated. Results regarding the ignition, combustion efficiency, combustor pressure loss, stability of combustion, and best configuration are provided.
Date:
November 30, 1955
Creator:
Wear, Jerrold D. & Smith, Arthur L.
Object Type:
Report
System:
The UNT Digital Library
Preliminary investigation of the effects of several seeker-nose configurations on the longitudinal characteristics of a canard-type missile at a Mach number of 1.60
Report presenting an investigation to determine the effect of several seeker-nose configurations on the static longitudinal stability, canard control characteristics, and lift and drag at Mach number 1.60 of a canard-type ramjet missile with 70 degree delta canard control surfaces and 70 degree delta wings. The tests indicate that, for the most part, the configurations tested exhibited no significant difference in static longitudinal stability or horizontal-canard control effectiveness.
Date:
October 30, 1953
Creator:
Robins, A. Warner
Object Type:
Report
System:
The UNT Digital Library
Experimental investigation of performance and operating characteristics of a tail-pipe burner for a turbojet engine
Report presenting an investigation to obtain fundamental information required for the design of a satisfactory tail-pipe burner for augmenting turbojet engine thrust. Investigations were also conducted to determine the combustion and pressure-drop characteristics of the most satisfactory burner, to develop a method of controlling the burner-outlet temperature distribution, and to improve the burner ignition characteristics.
Date:
October 30, 1947
Creator:
Gabriel, David S.; Martinson, E. Vincent & Essig, Robert H.
Object Type:
Report
System:
The UNT Digital Library