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Aeronautical Characteristics of a 45 Degree Sweptback Wing-Fuselage Combination and the Fuselage Alone Obtained in the Langley 8-Foot Transonic Tunnel

Description: Report presenting a fuselage and wing-fuselage combination with a wing of 45 degrees sweepback of the 0.25-chord line, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil sections in the slotted test section of a transonic tunnel for a range of Mach numbers and angles of attack. Results regarding lift characteristics, drag characteristics, lift-drag ratios, pitching-moment characteristics, a comparison with other test results, and base-pressure characteristics are provided.
Date: September 16, 1952
Creator: Osborne, Robert S. & Mugler, John P., Jr.
Item Type: Refine your search to only Report
open access

Aeronautical interference effects on normal and axial force coefficients of several engine-strut-body configurations at Mach numbers of 1.8 and 2.0

Description: Report presenting an investigation of the aerodynamic interference effects associated with a missile configuration, consisting of a pointed body of revolution with one or two ramjet engines strut-mounted in a vertical plane through the center line of the body, at several engine locations relative to the body and a range of angles of attack. The experimental data indicated increases in slope of the normal force curve with outward movement of the engines. Results regarding the characteristics of … more
Date: April 28, 1952
Creator: Kremzier, Emil J. & Dryer, Murray
Item Type: Refine your search to only Report
open access

Air Sampling Chamber for S.I.R.

Description: Abstract: An ionization chamber to monitor air for beta activity is described. Operating curves are given, as well as results of shock and vibration tests. Recommendation for improved design are included.
Date: August 8, 1952
Creator: Dewes, R. A. & Goodale, E. E.
Item Type: Refine your search to only Report
open access

Airborne Radioactivity Survey of Part of the Navajo Indian Reservation of Utah and Arizona

Description: From introduction: The purpose of an airborne radioactivity survey is to locate ground areas of higher than normal radioactivity which might lead to discovery of uranium mineralization. For this type of survey, gamma-ray detection equipment employing either a geiger counter or a scintillation counter can be mounted in a fixed wing aircraft or a helicopter.
Date: February 29, 1952
Creator: Cummings, Winthrop L.
Item Type: Refine your search to only Report
open access

Airborne Radioactivity Surveys in the Mojave Desert Region, Kern, Riverside, and San Bernardino Counties, California

Description: From abstract: Airborne radioactivity surveys in the Mojave Desert region, Kern, Riverside, and San Bernardino counties were made in five areas recommended as favorable for the occurrence of radioactive raw materials: (1) Rock Corral area, San Bernardino County. (2) Searles Station area, Kern County. (3) Soledad area, Kern County, (4) White Tank area, Riverside and San Bernardino counties. (5) Harvard Hills area, San Bernardino County. Anomalous radiation was detected in all but the Harvard Hil… more
Date: July 1952
Creator: Moxham, Robert Morgan
Item Type: Refine your search to only Report
open access

Airborne Radiometric Survey of the East Flank of the Big Horn Mountains, Wyoming and Montana

Description: Abstract: An airborne radiometric survey of parts of the east flank of the Big Horn Mountains was begun on June 23, and completed on August 27, 1952. An area of approximately 250 square miles was covered, and only two anomalies were found in the entire area. Flight lines were arranged in accordance with the geology of the area, particular attention being given to formations the stratigraphic equivalents of which are known to be uranium bearing in other areas. Two additional zones of radioactivi… more
Date: September 26, 1952
Creator: Jones, E. E.
Item Type: Refine your search to only Report
open access

Aircraft Nuclear Propulsion Project Quarterly Progress Report: Period Ending December 10, 1951

Description: This quarterly progress report details the ongoing research and experiments at the Oak Ridge National Laboratory as part of the Aircraft Nuclear Propulsion Project. The first part of this report discusses reactor theory and design. The second part of this report is not included. The third part of this report discusses materials research. The fourth part of this report includes appendixes
Date: March 6, 1952
Creator: Briant, R. C. & Cottrell, W. B.
Item Type: Refine your search to only Report
open access

Aircraft Nuclear Propulsion Project Quarterly Progress Report for Period Ending June 10, 1952

Description: This quarterly progress report details ongoing work at the Oak Ridge National Laboratory as part of the Aircraft Nuclear Propulsion Project. Topics of discussion include reactor theory and design, shielding research, materials research, appendixes with information on ongoing analytical chemical studies.
Date: August 5, 1952
Creator: Briant, R. C.; Buck, J. H.; Miller, A. J. & Cottrell, W. B.
Item Type: Refine your search to only Report
open access

Aircraft Nuclear Propulsion Project Quarterly Progress Report for Period Ending June 10, 1952

Description: 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.
Item Type: Refine your search to only Report
open access

Aircraft Nuclear Propulsion Project Quarterly Progress Report for Period Ending March 10, 1952

Description: This quarterly progress discusses the ongoing work at the Oak Ridge National Laboratory for the quarter ending in March 10, 1952. Topics discussed include reactor theory and design, shielding research, materials research, and includes appendixes with supplemental information.
Date: May 7, 1952
Creator: Briant, R. C.; Miller, A. J. & Cottrell, William B.
Item Type: Refine your search to only Report
open access

Aircraft Nuclear Propulsion Project Quarterly Progress Report: Period Ending September 10, 1951

Description: The first part of this quarterly progress report details reactor theory and design, discussing the aircraft reactor experiment, experimental reactor engineering, reactor physics, and critical experiments. The second part of this report is not included. The third part of this quarterly progress report details materials research, discussing corrosion research, physical properties and heat-transfer research, metallurgy and ceramics, chemistry of high-temperature liquids, and radiation damage. The … more
Date: January 9, 1952
Creator: Briant, R. C.; Ellis, C. B. & Cottrell, William B.
Item Type: Refine your search to only Report
open access

Airfoil profiles for minimum pressure drag at supersonic velocities: Application of shock-expansion theory, including consideration of hypersonic range

Description: From Summary: "A comparison of optimum profiles determined by the shock-expansion method of this report with corresponding profiles determined by the linearized-theory method of a previous report shows only small differences in shape at Mach numbers up to infinity even though the linearized theory at high supersonic Mach numbers breaks down completely insofar as the drag of the profile is concerned. Curves are presented which show that for thin airfoils the use of a trailing-edge thickness cons… more
Date: September 17, 1952
Creator: Chapman, Dean R.
Item Type: Refine your search to only Report
open access

Airfoil profiles for minimum pressure drag at supersonic velocities -- general analysis with application to linearized supersonic flow

Description: From Summary: "A theoretical investigation is made of the airfoil profile for minimum pressure drag at zero lift in supersonic flow. In the first part of the report a general method is developed for calculating the profile having the least pressure drag for a given auxiliary condition, such as a given structural requirement or a given thickness ratio. To illustrate the general method, the optimum airfoil, defined as the airfoil having minimum pressure drag for a given auxiliary condition, is ca… more
Date: 1952
Creator: Chapman, Dean R.
Item Type: Refine your search to only Report
open access

Alloys of Uranium with Zirconium, Chromium, Columbium, Vanadium, and Molybdenum

Description: Abstract: Information on five uranium binary alloy systems has been surveyed. These systems are the alloys of uranium with zirconium, chromium, columbium, vanadium, and molybdenum. The equilibrium diagrams are discussed, and where available, data have been included on diffusion studies, cladding experiments, and mechanical properties.
Date: June 19, 1952
Creator: Saller, Henry A. & Rough, Frank A.
Item Type: Refine your search to only Report
open access

Altitude Investigation of Gas Temperature Distribution at Turbine of Three Similar Axial-Flow Turbojet Engines

Description: An investigation of the effect of inlet pressure, corrected engine speed, and turbine temperature level on turbine-inlet gas temperature distributions was conducted on a J40-WE-6, interim J40-WE-6, and prototype J40-WE-8 turbojet engine in the altitude wind tunnel at the NACA Lewis laboratory. The engines were investigated over a range of simulated pressure altitudes from 15,000 to 55,000 feet, flight Mach numbers from 0.12 to 0.64, and corrected engine speeds from 7198 to 8026 rpm.
Date: August 6, 1952
Creator: Prince, W. R. & Schulze, F. W.
Item Type: Refine your search to only Report
open access

Altitude investigation of three flame-holder and fuel-systems configurations in a short converging afterburner on a turbojet engine

Description: From Introduction: "Previous investigations of a number of internal configurations in the same afterburner shell are reported in reference 1 and 2. In the investigation reported herein, the performance and operational characteristics of three afterburner internal configurations were evaluated."
Date: September 10, 1952
Creator: Braithwaite, Willis M.; Renas, Paul E. & Jansen, Emmert T.
Item Type: Refine your search to only Report
open access

Altitude operational characteristics of a prototype model of the J47D (RX1-1 and RX1-3) turbojet engines with integrated electronic control

Description: Report presenting an investigation of the altitude operational characteristics of a prototype model of the J47D turbojet engines, which includes an afterburner, a variable-area exhaust nozzle, and an integrated electronic control in an altitude wind tunnel. Results regarding compressor stall, compressor unstall, combustor blow-out during acceleration, stall and blow-out protection, acceleration characteristics, deceleration characteristics, and altitude starting characteristics, afterburner ope… more
Date: January 8, 1952
Creator: Bloomer, Harry E.; Conrad, E. William & Sobolewski, Adam E.
Item Type: Refine your search to only Report
open access

Altitude performance investigation of single- and double-annular turbojet-engine combustors with various size fuel nozzles

Description: From Introduction: "The purpose of the investigation conducted at the NACA Lewis laboratory and reported herein was to determine the improvements possible in full-scale turbojet-engine performance when a single-annular combustor with slotted air-inlet orifices was used."
Date: June 9, 1952
Creator: Harp, James L., Jr. & Vincent, Kenneth R.
Item Type: Refine your search to only Report
open access

Altitude performance investigation of two flame-holder and fuel-system configurations in short afterburner

Description: From Introduction: "The results of this complete evaluation of the altitude performance and operational characteristics of the two types of flame-holder and fuel-system configurations are reported herein.The starting limits of both configurations at a flight Mach number of 0.6 are also discussed."
Date: May 6, 1952
Creator: Huntley, S. C. & Wilsted, H. D.
Item Type: Refine your search to only Report
open access

Altitude performance of annular combustor type turbojet engine with JFC-2 fuel

Description: An investigation was made comparing the performance of JFC-2 fuel and unleaded, clear gasoline in a 3000-pound-thrust turbojet engine. The JFC-2 fuel was a blend of percent diesel fuel and 25 percent aviation gasoline. Engine combustion efficiency was equal to that obtained with gasoline at rated engine speed and altitudes up to 35,000 feet, but at lower engine speeds or at higher altitudes the JFC-2 fuel gave lower combustion efficiency. No discernible difference was obtained in starting or lo… more
Date: February 5, 1952
Creator: Useller, James W.; Harp, James L., Jr. & Barson, Zelmar
Item Type: Refine your search to only Report
open access

Altitude Starting Tests of a 1000-Pound-Thrust Solid-Propellant Rocket

Description: Four solid-propellant rocket engines of nominal 1000-pound-thrust were tested for starting characteristics at pressure altitudes ranging from 112,500 to 123,000 feet and at a temperature of -75 F. All engines ignited and operated successfully. Average chamber pressures ranged from 1060 to ll90 pounds per square inch absolute with action times from 1.51 to 1.64 seconds and ignition delays from 0.070 t o approximately 0.088 second. The chamber pressures and action times were near the specificatio… more
Date: August 27, 1952
Creator: Sloop, John L.; Rollbuhler, R. James & Krawczonek, Eugene M.
Item Type: Refine your search to only Report
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