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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
Partner: UNT Libraries Government Documents Department
open access

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

Description: "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 a… more
Date: January 9, 1952
Creator: Schramm, Wilson B. & Ziemer, Robert R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Supplementary Free-Spinning-Tunnel Investigation of a 1/20-Scale Model of the McDonnell F2H-3 Airplane With External Stores Installed

Description: 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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of the Static Lateral Stability Characteristics of Wing-Fuselage Combinations at High Subsonic Speeds: Sweep Series

Description: Report presenting an investigation in the high-speed tunnel to determine the effect of sweep on the static lateral stability characteristics of wing-fuselage combinations with wings of aspect ratio 4 and taper ratio 0.6 at high subsonic speeds. Results regarding rolling-moment characteristics and lateral-force and yawing-moment characteristics are also provided.
Date: September 9, 1952
Creator: Kuhn, Richard E. & Fournier, Paul G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Lift, drag and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds: Plane tapered wing of aspect ratio 3.1 with 3-percent-thick rounded-nose section

Description: Report presenting a wing-body combination with a plane tapered wing of aspect ratio 3.1, taper ratio of 0.39, and 3-percent-thick, rounded-nose sections in streamwise planes at subsonic and supersonic Mach numbers. The lift, drag, and pitching moment are presented for a range of Mach numbers and Reynolds numbers.
Date: July 9, 1952
Creator: Heitmeyer, John C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of twist and camber, fences, and horizontal-tail height on the low-speed longitudinal stability characteristics of a wing-fuselage combination with a 45 degree sweptback wing of aspect ratio 8 at a Reynolds number of 4.0 x 10(exp 6)

Description: Report presenting an investigation of the separate and combined effects of twist and camber, fences, and horizontal-tail height on the static longitudinal stability of a 45 degree sweptback wing-fuselage combination of aspect ratio 8 at Mach number 0.19. Two different wings were investigated, one untwisted and one with twist and cambered. Results regarding wing-fuselage configuration and wing-fuselage configurations with horizontal tail are provided.
Date: December 9, 1952
Creator: Foster, Gerald V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Over-all performance of the J71 three-stage turbine

Description: Report presenting an investigation to determine the overall performance of the three-stage turbine from the J71 turbojet engine. The turbine operated with a maximum brake internal efficiency of approximately 0.84 at an equivalent overall pressure ratio of approximately 3.6 and an equivalent rotor speed of about 110 percent of the equivalent design value.
Date: July 9, 1952
Creator: Berkey, William E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of the hydrodynamic stability and resistance of two streamline fuselages

Description: Report presenting an investigation of a dynamic model to determine the effects of hull form, gross load, and aerodynamic trimming moments on the trim limits, trim, hydrodynamic moment, hydrodynamic resistance, total resistance, and rise of two streamline fuselages modified by chine strips. Results regarding effects of hull form and effects of gross load are provided.
Date: April 9, 1952
Creator: Weinflash, Bernard & Shuford, Charles L., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Effect of Entrance Mach Number and Lip Shape on the Subsonic Characteristics of a Scoop-Type-Air-Induction System for a Supersonic Airplane

Description: Report presenting an investigation at subsonic speeds to determine the effects of lip shape and entrance Mach number on the characteristics of a scoop-type air-induction system designed for an airplane flying at supersonic speeds. Results regarding the ram-recovery ratio, static-pressure distribution, and drag are provided.
Date: January 9, 1952
Creator: Holzhauser, Curt A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An analysis of the potentialities of a two-stage counterrotating supersonic compressor

Description: From Introduction: "The supersonic axial-flow compressor, for example, appears to offer advantages of high stage pressure ratio and height weight flows (reference 1) but problems peculiar to this compressor type have accompanied its introduction. For high single-stage pressure ratios (>4) the problem of converting the high dynamic energy to useful pressure arises (reference 2). In addition, the high tip speeds and weight flows combine to create a difficult situation for the turbine designer."
Date: July 9, 1952
Creator: Wilcox, Ward W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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
Partner: UNT Libraries Government Documents Department
open access

Gust-Tunnel Investigation of a Delta-Wing Model With the Leading Edge Swept Back 60 Degrees

Description: Report discussing an investigation of a delta-wing model with the leading edge swept back 60 degrees. Testing indicated that the gust load is greater than would be predicted by using a slope of the lift curve determined from steady-flow force tests. An aspect-ratio relation was determined for this type of wing with the selected apex angle, but it does not appear to be applicable to other wings with different apex angles.
Date: April 9, 1952
Creator: Pierce, Harold B. & Johns, Slaton L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Ignition delay experiments with small-scale rocket engine at simulated altitude conditions using various fuels with nitric acid oxidants

Description: "Ignition delay determinations of several fuels with nitric oxidants were made at simulated altitude conditions utilizing a small-scale rocket engine of approximately 50 pounds thrust. Included in the fuels were aniline, hydrazine hydrate, furfuryl alcohol, furfuryl mercaptan, turpentine, and mixtures of triethylamine with mixed xylidines and diallyaniline. Red fuming, white fuming, and anhydrous nitric acids were used with and without additives. A diallylaniline - triethylamine mixture and a r… more
Date: January 9, 1952
Creator: Ladanyi, Dezso J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance of the Components of the XJ34-WE-32 Turbojet Engine Over a Range of Engine and Flight Conditions

Description: Performance of the compressor, combustor, and turbine operating as integral parts of the XJ34-WE-32 turbojet engine was determined in the Lewis altitude wind tunnel over a range of altitudes from 5000 to 55,000 feet and flight Mach numbers from 0.28 to 1.05. Data were obtained for each of four exhaust-nozzle areas and are presented in graphical and tabular form.
Date: June 9, 1952
Creator: McAulay, John E.; Sobolewski, Adam E. & Smith, Ivan D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Supplementary Free-Spinning-Tunnel Investigation of a 1/20-Scale Model of the McDonnell F2H-3 Airplane with External Stores Installed: TED No. NACA DE 2393

Description: Memorandum presenting a supplementary investigation conducted in the 20-foot free-spinning tunnel to determine the effect of external stores and lateral center-of-gravity displacement upon the spin and spin-recovery characteristics of a 1/20-scale model of the McDonnell F2H-3 airplane. Results regarding the tests with wing-tip tanks installed and with the experimental aerodynamic shape installed are provided.
Date: June 9, 1952
Creator: Wilson, Jack H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary free-flight investigation of the zero-lift drag penalties of several missile nose shapes for infrared seeking devices

Description: The results of a preliminary investigation to develop a nose shape suitable for housing an infrared seeker are presented. The zero-lift drag characteristics of a missile-like body with various unconventional nose shapes were obtained through a range of Mach numbers from 0.8 to 1.8 and Reynolds numbers, based on body length, from 20 x10 to the 6th power to 70 x 10 to the 6th power, respectively, by using rocket-propelled free-flight models. Results of the test indicate that at supersonic speeds … more
Date: December 9, 1952
Creator: Piland, Robert O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Cloverleaf Cyclotron Three Phase Radiofrequency System

Description: The geometry of the magnetic pole structure in the cloverleaf cyclotron suggests the use of three dees excited by three phase rf placed in the valleys out of the way of the beam. Experience with the model machines indicates that it is desirable to be able to vary the phase angles between the three dee voltages through 30 or 40 degrees and to be able to maintain them at any given value within plus or minus one degree. It is desirable, also, to be able to vary the phase angle independently of the… more
Date: September 9, 1952
Creator: Smith, Bob H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Process Engineering Report, Operating Manual for Supervisory Personnel, Raw Materials Feed Preparation Plant, Process and Operating Equipment. Part II

Description: This technical report presents necessary information required to operate the raw materials feed preparation plant. The information herein is intended to serve as a guide to operating personnel and to provide general data concerning the process.
Date: December 9, 1952
Creator: Lukens, R. P.; Abrams, S. H.; Carr, H. R.; Lindsey, P. S.; Grimac, T. E.; Knoll, F. J. et al.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Homogeneous Reactor Project Quarterly Progress Report for Period Ending August 15, 1951

Description: Technical report focusing on the Homogeneous Reactor Experiment (HRE) construction, completed 60% as of August 15, 1951. Report also includes alternate systems studies and long range studies of the Homogeneous Reactor Experiment. Technical report is organized in three parts. [From Summary]
Date: January 9, 1952
Creator: Thompson, W. E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Recovery of Uranium by Ion Exchange or by Uranous Phosphate Precipitation from Sulfuric Acid Leach Solutions Produced from Australian Davidite Ore Concentrates

Description: Uranium ore from Radium Hill, South Australia was leached with hot sulfuric acid solutions and the uranium recovered from solution by uranous phosphate precipitation or by use of anion exchange resins.
Date: June 9, 1952
Creator: George, D'Arcy R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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