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Serial/Series Title
NACA Research Memorandums
192
Atomic Energy Commission Reports
99
Hanford Works Reports
22
NACA Technical Reports
22
HW (Series)
17
University of California Radiation Laboratory Reports
16
Oak Ridge National Laboratory Reports
15
BNL (Series)
12
Brookhaven National Laboratory Reports
12
Report (U.S. Atomic Energy Commission)
12
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An 8-Foot Axisymmetrical Fixed Nozzle for Subsonic Mach Numbers Up to 0.99 and for a Supersonic Mach Number of 1.2
From Introduction: "This paper, which should be of interest to those concerned with transonic wind tunnels, covers the design and operating characteristics of the nozzle."
Date:
February 23, 1950
Creator:
Ritchie, Virgil S.; Wright, Ray H. & Tulin, Marshall P.
Object Type:
Report
System:
The UNT Digital Library
1706-KER Coolant Test Facility Operations Manual
This procedure is intended to be used as: 1. An instruction and guide for operation of the KER loops. 2. To aid in familiarization and understanding of the general operation of the loops. 3. To prevent lost time due to errors in loop operation. The procedure is not meant to be completely comprehensive in all details of loop operation.
Date:
January 23, 1958
Creator:
Dulin, R. V.
Object Type:
Report
System:
The UNT Digital Library
Absolute Cross Sections of the Reaction P + P - w+ + d
Absolute differential cross sections for the reaction p + p - w+ + d were obtained by detecting meson-deuteron coincidences produced by passing the 340-Mev external proton beam of the Berkeley synchro-cyclotron through a liquid hydrogen target.
Date:
April 23, 1953
Creator:
Crawford, Frank Stevens, Jr.
Object Type:
Report
System:
The UNT Digital Library
Additional Results in a Free-Flight Investigation of Control Effectiveness of Full-Span, 0.2-Chord Plain Ailerons at High Subsonic, Transonic, and Supersonic Speeds to Determine Some Effects of Wing Sweepback, Aspect Ratio, Taper, and Section Thickness Ratio
Report discussing an aerodynamic control effectiveness study using free-flight, rocket-propelled test vehicles. Information about the effects of wing sweepback, aspect ratio, taper ratio, and section thickness ratio on the rolling effectiveness of full-span, sealed ailerons is provided.
Date:
April 23, 1948
Creator:
Sandahl, Carl A. & Strass, H. Kurt
Object Type:
Report
System:
The UNT Digital Library
Advanced Indirect Cycle Water Reactor Studies for Maritime Applications: Part 3. Analog Simulation of Reactor Plant Transients
Third part of the "final report of a study directed toward the evolution, design, and demonstration of the principle design features of interim indirect cycle water cooled and moderated nuclear power plants which will be useful in early cooperative programs between the Atomic Energy Commission and the United States maritime industry" (p. i).
Date:
October 23, 1961
Creator:
Combustion Engineering, inc. Nuclear Division.
Object Type:
Report
System:
The UNT Digital Library
Advanced Indirect Cycle Water Reactor Studies for Maritime Applications: Part 4. Steam Driven Coolant Pumps
Fourth part of the "final report of a study directed toward the evolution, design, and demonstration of the principle design features of interim indirect cycle water cooled and moderated nuclear power plants which will be useful in early cooperative programs between the Atomic Energy Commission and the United States maritime industry" (p. i).
Date:
October 23, 1961
Creator:
Combustion Engineering, inc. Nuclear Division.
Object Type:
Report
System:
The UNT Digital Library
Advanced Indirect Cycle Water Reactor Studies for Maritime Applications: Part 5. Spiked Core Concept
Fifth part of the "final report of a study directed toward the evolution, design, and demonstration of the principle design features of interim indirect cycle water cooled and moderated nuclear power plants which will be useful in early cooperative programs between the Atomic Energy Commission and the United States maritime industry" (p. i).
Date:
October 23, 1961
Creator:
Combustion Engineering, inc. Nuclear Division.
Object Type:
Report
System:
The UNT Digital Library
Aerial Radiometric and Magnetic Survey: Crystal City National Topographic Map, Texas Gulf Coast, Volume 1
Final report documenting a high-sensitivity airborne gamma radiation and magnetic field survey of the Texas portions of the Crystal City (NH 14-11 quadrangle) National Topographic Map segment including a description of the program and results.
Date:
May 23, 1979
Creator:
Geodata International
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic and hydrodynamic characteristics of a proposed supersonic multijet water-based hydro-ski aircraft with a variable-incidence wing
From Introduction: "The configuration described in this paper represents one approach to such an airplane and the results of the wind-tunnel and tank evaluations are presented. In the present investigation, the aerodynamic longitudinal characteristics over a Mach number range from 0.6 to 1.97 were obtained."
Date:
October 23, 1957
Creator:
Petynia, William W.; Hasson, Dennis F. & Spooner, Stanley H.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic Characteristics at High and Low Subsonic Mach Numbers of the NACA 0012, 64₂-015, and 64₃-018 Airfoil Sections at Angles of Attack from -2 Degrees to 30 Degrees
An investigation has been made in the Langley low-turbulence pressure tunnel of the aerodynamic characteristics of the NACA 0012, 64(sub 2)-015, and 64(sub 3)-018 airfoil sections. Data were obtained at Mach numbers from 0.3 to that for tunnel choke, at angles of attack from -2deg to 30deg, and with the surface. of each airfoil smooth-and with roughness applied at the leading edge.The Reynolds numbers of the tests ranged from 0.8 x 10(exp 6) to 4.4 x 10(exp 6). The results are presented as variations of lift, drag, and quarter-chord pitching-moment coefficients with Mach number.
Date:
July 23, 1954
Creator:
Critzos, Chris C.
Object Type:
Report
System:
The UNT Digital Library
The Aerodynamic Characteristics in Pitch of a 1/15-Scale Model of the Grumman F11F-1 Airplane at Mach Numbers of 1.41, 1.61, and 2.01, TED No. NACA DE 390
"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 to determine the static longitudinal stability and control characteristics of various arrangements of the Grumman F11F-1 airplane. Tests were made of the complete model and various combinations of its component parts and, in addition, the effects of various body modifications, a revised vertical tail, and wing fences on the longitudinal characteristics were determined" (p. 1).
Date:
May 23, 1956
Creator:
Driver, Cornelius
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic Characteristics of a 42 Degree Swept-Back Wing With Aspect Ratio 4 and NACA 64(Sub 1)-112 Airfoil Sections at Reynolds Numbers From 1,700,000 to 9,500,000
Report discussing testing on a 42 degree swept-back wing to determine its low-speed aerodynamic characteristics in pitch and yaw at high Reynolds numbers. The main effect of increasing the Reynolds number was delayed wing stalling to higher angles of attack. Roughness on the wing leading edge also had a large adverse effect on lift, drag, and pitching-moment characteristics at higher Reynolds numbers.
Date:
May 23, 1947
Creator:
Neely, Robert H. & Conner, D. William
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic Characteristics of a Flying-Boat Hull Having a Length-Beam Ratio of 15, TED No. NACA 2206
"An investigation was made in the Langley 300 MPH 7- by 10-foot tunnel to determine the aerodynamic characteristics of a flying-boat hull of a length-beam ratio of 15 in the presence of a wing. The investigation was an extension of previous tests made on hulls of length-beam ratios of 6, 9, and 12; these hulls were designed to have approximately the same hydrodynamic performance with respect to spray and resistance characteristics. Comparison with the previous investigation at lower length-beam ratios indicated a reduction in minimum drag coefficients of 0.0006 (10 percent) with fixed transition when the length-beam ratio was extended from 12 to 15" (p. 1).
Date:
January 23, 1951
Creator:
Riebe, John M. & Naeseth, Rodger L.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic Characteristics of Two Delta Wings at Mach Number 4.04 and Correlations of Lift and Minimum-Drag Data for Delta Wings at Mach Numbers From 1.62 to 6.9
Report presenting tests of the aerodynamic characteristics of two delta wings of the same aspect ratio and airfoil sections at Mach number 4.04. The results indicated that the ratio of the experimental lift-curve slope to the theoretical two-dimensional lift-curve slope from previous testing is valid at this Mach number.
Date:
December 23, 1952
Creator:
Ulmann, Edward F. & Dunning, Robert W.
Object Type:
Report
System:
The UNT Digital Library
The Aerodynamic Effects of Rockets and Fuel Tanks Mounted Under the Swept-Back Wing of an Airplane Model
From Summary: "The effects of externally mounted rockets and fuel tanks on the aerodynamic characteristics of an airplane model with a swept-back wing are presented in this report."
Date:
April 23, 1948
Creator:
Boddy, Lee E. & Morrill, Charles P., Jr.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic Load Measurements Over a Leading-Edge Slat on a 40 Degree Sweptback Wing at Mach Numbers From 0.10 to 0.91
Report presenting an investigation of the aerodynamic loads on a leading-edge slat on a 40 degree sweptback wing with NACA 64(sub 1)-112 airfoil sections in the low-turbulence pressure tunnel. Results regarding wing force data, slat force data, and slat pressure distributions are provided.
Date:
September 23, 1952
Creator:
Cahill, Jones F. & Nuber, Robert J.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic Loads on Tails at High Angles of Attack and Sideslip
"Results are presented for the loads and moments acting on the individual tail surfaces of a body-tail combination over a wide range of angles of attack and sideslip. The effects of forebody length and panel-panel interference on the characteristics are included. It is shown that large nonlinear variations in these loads and moments, which occur at some combinations of angle of attack and sideslip, cannot be predicted by low-angle theory" (p. 1).
Date:
July 23, 1957
Creator:
Spahr, J. Richard & Polhamus, Edward C.
Object Type:
Report
System:
The UNT Digital Library
An Airborne Simulator Investigation of the Accuracy of an Optical Track Command Missile Guidance System
Memorandum presenting an airborne missile simulator used to represent visually the predicted flight behavior of the Navy XASM-N-7 Bullpup air-to-surface missile, which is guided along the line of sight to the target by bang-bang radio signals controlled by the pilot of the launch airplane. Quantitative response measurements showed that the simulator gave a good representation of the trajectory and control characteristics predicted for the Bullpup missile, and the simulation appeared plausible to the pilots.
Date:
November 23, 1956
Creator:
Douvillier, Joseph G., Jr.; Foster, John V. & Drinkwater, Fred J., III
Object Type:
Report
System:
The UNT Digital Library
Aircraft Nuclear Propulsion Project Quarterly Progress Report for Period Ending June 10, 1952
This quarterly progress details ongoing research at the Oak Ridge National Laboratory as a part of the Aircraft Nuclear Propulsion Project. Topics discussed include reactor theory and design, [part two is not included], materials research, and appendixes with information on analytical chemical studies.
Date:
October 23, 1952
Creator:
Briant, R. C.; Buck, J. H.; Miller, A. J. & Cottrell, William B.
Object Type:
Report
System:
The UNT Digital Library
Airplane Measurements of Atmospheric Turbulence for Altitudes Between 20,000 and 55,000 Feet Over the Western Part of the United States
Report presenting a sample of data on atmospheric turbulence on Lockheed U-2 airplanes during research flights. The intensity, amount, and extent of atmospheric turbulence observed in the United States is in good agreement with data from England and Western Europe. Results regarding overall gust distribution, intensity of turbulence, percent of rough air, and size of turbulent areas are provided.
Date:
August 23, 1957
Creator:
Coleman, Thomas L. & Coe, Emilie C.
Object Type:
Report
System:
The UNT Digital Library
Alternate Acid Addition Facility for 100-K
Document HW-33176, "A Proposed Scope of the 100-K Sulfuric Acid Addition Facilities", presented the justification and bases for a sulfuric acid addition facility at the 183-K headhouses and included a system for adding the acid to the raw water. Since the issue of this document several factors to consider in such a system have been brought to light by experience gained both at K and at other areas. The alternate system presented here eliminates several of the troublesome points in the previously proposed system.
Date:
August 23, 1955
Creator:
Bainard, W. D.
Object Type:
Report
System:
The UNT Digital Library
Altitude-chamber performance of British Rolls-Royce Nene II engine 1: standard 18.75-inch-diameter jet nozzle
Report presenting an altitude-chamber investigation to determine the altitude performance characteristics of the British Rolls-Royce Nene II turbojet engine with a standard 18.75-inch-diameter jet nozzle. Results regarding the simulated flight performance and generalized performance across other altitude and pressure characteristics are provided.
Date:
September 23, 1949
Creator:
Barson, Zelmar & Wilsted, H. D.
Object Type:
Report
System:
The UNT Digital Library
Altitude evaluation of several afterburner design variables on a J47-GE-17 turbojet engine
From Introduction: "The investigation reported herein presents information on design factors and modifications of the production afterburner for the J47-GE-17 turbojet engine designed for medium temperature operation. The present report is concerned only with the afterburner performance and operating characteristics.Altitude-starting characteristics of two of the configurations in this report are discussed in reference 1."
Date:
October 23, 1953
Creator:
Braithwaite, Willis M.; Walker, Curtis L. & Sivo, Joseph N.
Object Type:
Report
System:
The UNT Digital Library
Altitude-ignition limit of a turbojet engine using a condenser-discharge ignition system
The altitude-ignition limits of a condenser-discharge ignition system installed on a turbojet engine were determined at a flight Mach number of 0.6 using 1.1-pound Reid vapor pressure fuel. Ignition was possible up to an altitude of 55,000 feet with 4.8 joules per spark and 6 sparks per second.
Date:
October 23, 1951
Creator:
Armstrong, John C.
Object Type:
Report
System:
The UNT Digital Library