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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.
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.
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.
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.
open access

ALTERNATE VALVE STUDIES

Description: No Description Available.
Date: April 15, 1952
Creator: McLean, H.J. & Wirta, R.W.
open access

Alternative Filter Equipment for Ventilation Air of Separations Plants

Description: The objective of this report is to review the performance of the Redox air-filtration facilities and to present recommendations, resulting from this survey, which could improve the ventilation systems of future Separations Plants. 4 refs., 3 figs., 2 tabs.
Date: December 8, 1952
Creator: Blasewitz, A. G.
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.
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.
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.
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
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.
open access

Altitude Wind Tunnel Investigation of High-Temperature Afterburners

Description: From Introduction: "During previous investigations of afterburning conducted at the NACA Lewis laboratory (references 1 to 4, for example), the objective of obtaining high exhaust-gas temperatures and, consequently, maximum thrust augmentation was compromised to some extent in order to alleviate the problem of afterburner shell cooling. The primary objective of the investigation reported herein was therefore the attainment of maximum exhaust-gas temperature imposed by the cooling techniques pre… more
Date: June 26, 1952
Creator: Conrad, E. William & Campbell, Carl E.
open access

Aluminium Corrosion in High Purity Water

Description: Summary: "A corrosion test of aluminum components in a 4-ft. section of a fuel tube has been tested under conditions simulating plant geometry and, as nearly as possible, the operating conditions of water purity, temperature, and flow rate. Results: 1. None of the aluminum components, 63S fuel tube, 2S solid fillers and 43S spacers showed any corrosion effects beyond normal oxide film formation. This was carried out in flowing water, maintained at a specific resistivity greater than 1 x 10(… more
Date: May 1952
Creator: Nielsen, N. A.
open access

The Ames supersonic free-flight wind tunnel

Description: From Introduction: "Because of the unusual nature of this equipment, and because it is proving to be very useful for certain kinds of aerodynamic research, this report has been prepared. It contains a description of the equipment and its use to obtain aerodynamic coefficients. The imperfections in the wind-tunnel air stream and their effect on model tests are also discussed."
Date: April 25, 1952
Creator: Seiff, Alvin; James, Carlton S.; Canning, Thomas N. & Boissevain, Alfred G.
open access

The Ames Supersonic Free-Flight Wind Tunnel

Description: Memorandum presenting a description of the Ames supersonic free-flight wind tunnel, which is a new piece of equipment for aerodynamic research at high supersonic Mach numbers. It has a wide Mach number range extending from low supersonic speeds to Mach numbers in excess of 10. The air stream in the tunnel is imperfect, mainly due to a symmetrical pair of oblique shock waves which reflect down the test section.
Date: April 25, 1952
Creator: Seiff, Alvin; James, Carlton S.; Canning, Thomas N. & Boissevain, Alfred G.
open access

Amplitude of Supersonic Diffuser Flow Pulsations

Description: "A theoretical method for evaluating the stability characteristics and the amplitude and the frequency of pulsation of ram-jet engines without heat addition is presented herein. Experimental verification of the theoretical results are included where data were available. Theory and experiment show that the pulsation amplitude of a high mass-flow-ratio diffuser having no cone surface flow separation increases with decreasing mass flow" (p. 1).
Date: December 16, 1952
Creator: Sterbentz, William H. & Davids, Joseph
open access

Analogue-computer simulation of an autopilot servo system having nonlinear response characteristics

Description: From Introduction: "The servo system considered in this report is in the latter category, due mainly to the fact its amplifier tends to saturate. An investigation of the longitudinal dynamic response of the stabilized airplane was made and the results were reported in reference 1. In this investigation it was found that when restricted to linear methods of analysis the performance of the autopilot-aircraft combination could be predicted for only the small range of operation where the elements o… more
Date: June 1952
Creator: Jones, Arthur L. & White, John S.
open access

Analyses of Foreign Coals

Description: Report summarizing analyses through tables and maps of foreign coals.
Date: 1952
Creator: Morgan, R. E. & Barkley, J. F.
open access

Analyses of Ohio Coals

Description: Report discussing an analyses of the data for Ohio coals, which the Bureau of Mines providing an analysis of every coal-mining State.
Date: 1952
Creator: Fieldner, A. C.; Taylor, Dorothy Ann; Toenges, Albert L.; Crentz, William L.; Fraser, Thomas; Young, W. H. et al.
open access

Analysis of a liquid-metal turbine-propeller cycle for propulsion of low-speed nuclear- powered aircraft

Description: From Introduction: "The intermediate subsonic speed range is considered and the liquid-metal turbine-propeller cycle discussed in this report. In this report, compressor pressure ratio, heat-exchanger air-inlet Mach number, and turbine-inlet temperature were optimized for maximum engine net thrust per engine-plus-heat exchanger weight (minimum airplane gross weight) for a range of heat-exchanger effective wall temperature."
Date: May 27, 1952
Creator: Rom, F. E. & Wachtl, W. W.
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