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"25" Critically Consultation with J. W. Morfitt : April 3, 1950

Description: Summary: "Criticality was considered impossible in any contingency encountered in practice under either of the following conditions which include no safety factor: (a) In any isolated cylinder not more than 5 in. in disruptor, if the total amount of U235 present does not exceed 7.5 Eg. (b) In an isolated vessel of any shape and size, if the total amount of U235 present does not exceed 880 g. An "isolated" vessel is one which does not "see" more than 0.1 [...] other vessels containing fissionabl… more
Date: April 3, 1950
Creator: Merrill, E. T. & Sege, G.
Item Type: Refine your search to only Report
open access

Aerodynamic characteristics at Reynolds numbers of 3.0 x 10(exp 6) and 6.0 x 10(exp 6) of three airfoil sections formed by cutting off various amounts from the rear portion of the NACA 0012 airfoil section

Description: Report presenting an investigation of the two-dimensional aerodynamic characteristics of three airfoil sections formed by removing various portions of the original chord from the trailing edge of the NACA 0012 airfoil section. Results regarding lift, drag, and pitching moment and aerodynamic center are provided.
Date: April 1950
Creator: Smith, Hamilton A. & Schaefer, Raymond F.
Item Type: Refine your search to only Report
open access

Altitude performance and operational characteristics of 29-inch-diameter tail-pipe burner with several fuel systems and fuel-cooled stage-type flame holders on J35-A-5 turbojet engine

Description: An investigation of tail-pipe burning was conducted in the NACA Lewis altitude wind tunnel with a full-scale turbojet engine and an 29-inch-diameter tail-pipe burner. Effects of fuel distribution and number and arrangement of stages on performance and operational characteristics of several fuel-cooled flame holders are presented and discussed. Operation with a three-stage flame holder having the large stage upstream was the most efficient. Combustion efficiency was slightly increased at high al… more
Date: April 28, 1950
Creator: Golladay, Richard L. & Bloomer, Harry E.
Item Type: Refine your search to only Report
open access

Amplitude distribution and energy balance of small disturbances in plate flow

Description: From Introduction: "The present report, therefore, deals first, with the distribution of the amplitude of the disturbance over the flow section, that is, the calculation of the characteristic functions and second, with the study of the energy distribution and energy balance of the disturbance motion. The investigations are based upon the disturbances of the laminar flow past a flat plate which are situated exactly at the boundary between amplification and damping (neutral oscillations)."
Date: April 1950
Creator: Schlichting, H.
Item Type: Refine your search to only Report
open access

Analysis of an induction blowdown supersonic tunnel

Description: From Introduction: "In the present paper, general ejector equations (see reference 4 or 5) and certain assumptions with regard to flow conditions and pressure losses have been utilized to calculate the running times of induction blowdown supersonic tunnels operating in the mentioned Mach number range."
Date: April 1950
Creator: Bidwell, Jerold M.
Item Type: Refine your search to only Report
open access

Analytical and experimental investigation of thrust augmentation of axial- and centrifugal-compressor turbojet engines by injection of water and alcohol in combustion chambers

Description: Report presenting an investigation of thrust augmentation by injection of water and water-alcohol mixtures in the combustion chambers at sea-level zero-ram flight conditions on 4000-pound-thrust axial-flow and centrifugal-flow turbojet engines. Thrust augmentation, compressor characteristics, fuel flow, and turbine-outlet-temperature distributions are presented for various injection rates and water-alcohol mixtures.
Date: April 13, 1950
Creator: Gabriel, David S.; Dowman, Harry W. & Jones, William L.
Item Type: Refine your search to only Report
open access

Analytical determination of local surface heat-transfer coefficients for cooled turbine blades from measured metal temperatures

Description: From Summary: "Procedures for applying these analytical methods to experimentally measured blade-metal temperatures are presented. Data are presented for the leading and trailing edge of a symmetrical water-cooled blade to illustrate the validity of the methods for those portions of the blade. In addition to the application to turbine blades, the methods can be applied to any heat-transfer apparatus having a profile that can be approximated by the shape discussed."
Date: April 10, 1950
Creator: Brown, W. Byron & Esgar, Jack B.
Item Type: Refine your search to only Report
open access

A comparison of theoretical and experimental wing bending moments during seaplane landings

Description: Report presenting a smooth-water-landing investigation with a small seaplane to obtain experimental wing-bending-moment time histories together with time histories of the various parameters necessary for the prediction of wing bending moments during hydrodynamic impact. Experimental results were compared with calculated results, including inertia-load effects and the effects of air-load variation during impact.
Date: April 1950
Creator: Merten, Kenneth F.; RodrÍguez, José L. & Beck, Edgar B.
Item Type: Refine your search to only Report
open access

Correlation of effects of fuel-air ratio, compression ratio, and inlet-air temperature on knock limits of aviation fuels

Description: Report presenting a method of relating the effects of fuel-air ratio on the knock-limited charge flow and power of a supercharged engine with those of compression ratio and inlet-air temperature. Knock data obtained in a CFR engine over a wide range of conditions were correlated with eight fuels: 28-R fuel, aviation alkylate, S reference fuel, diisopropyl, triptane, cyclohexane, cyclopentane, and triptene.
Date: April 1950
Creator: Tower, Leonard K. & Alquist, Henry E.
Item Type: Refine your search to only Report
open access

Corrosion of Austenitic Stainless Steels in MJ-4 Raw Streams

Description: Introduction: "A laboratory investigation of the relative corrosion resistance of several austenitic stainless steels to the RAW stream of the Tributyl Phosphate Waste Metal Recovery Process was made during the first quarter of 1950. The results of this investigation are reported herein; all original data are recorded in laboratory notebook HW-3282-T."
Date: April 25, 1950
Creator: Koenig, W. W.
Item Type: Refine your search to only Report
open access

Cylinder-head temperatures and coolant heat rejection of a multicylinder liquid-cooled engine of 1650-cubic-inch displacement

Description: Report presenting an investigation of the cooling characteristics of a multicylinder liquid-cooled engine of 1650-cubic-inch displacement. The results showing the variation of the cylinder-head temperature and the coolant heat rejection with the pertinent engine and coolant variables are provided. Data included a variety of engine power outputs, engine speeds, manifold pressure, fuel-air ratio, inlet-air temperature, ignition timing, exhaust pressure, coolant flow, composition, temperature, and… more
Date: April 1950
Creator: Povolny, John H.; Bogdan, Louis J. & Chelko, Louis J.
Item Type: Refine your search to only Report
open access

Ditching Tests of a 1/18-Scale Model of the Lockheed Constellation Airplane

Description: "Tests were made of a 1/18-scale dynamically similar model of the Lockheed Constellation airplane to investigate its ditching characteristics and proper ditching technique. Scale-strength bottoms were used to reproduce probable damage to the fuselage. The model was landed in calm water at the Langley tank no. 2 monorail. Various landing attitudes, speeds, and fuselage configurations were simulated" (p. 1).
Date: April 20, 1950
Creator: Fisher, Lloyd J. & Morris, Garland J.
Item Type: Refine your search to only Report
open access

The effect of accelerating a hypothetical aircraft through the transonic range with controls fixed

Description: Memorandum presenting Mach number histories of the motion experienced by a hypothetical, small, straight-wing aircraft accelerating at various rates through an assumed controls-fixed pitch-down balance change in the transonic range. Two approximate analytical solutions of the longitudinal equations of motion are developed which are based on certain simplifying assumptions indicated by the differential-analyzer results.
Date: April 4, 1950
Creator: Matthews, Howard F.
Item Type: Refine your search to only Report
open access

Effect of air distribution on radial temperature distribution in one-sixth sector of annular turbojet combustor

Description: Report presenting an experimental investigation in a one-sixth sector of an annular turbojet combustor to determine a method of controlling radial exhaust-gas-temperature distribution in a gas-turbine combustion chamber. The adjustment in controlling air was made by ducting the dilution air into the combustion zone in a predetermined manner through hollow radial struts or by modifying the basket-wall open-hole area. Results regarding the temperature distribution, temperature-rise efficiency, to… more
Date: April 5, 1950
Creator: Mark, Herman & Zettle, Eugene V.
Item Type: Refine your search to only Report
open access

The effect of pile gas on tube block temperatures in {open_quotes}G{close_quotes} pile

Description: Helium, carbon dioxide, and helium-carbon dioxide mixtures are being considered for use as the pile gas in `G` pile. Coring the graphite tube block to provide a gas gap between the process tube centered in the graphite and the graphite tube block has been suggested as a means of maintaining high graphite temperatures in the tube blocks. It has been established that graphite damage during irradiation in minimized at high temperatures.
Date: April 7, 1950
Creator: Sega, C. A.
Item Type: Refine your search to only Report
open access

The Effect of Spanwise Aileron Location on the Rolling Effectiveness of Wings With 0 Degree and 45 Degree Sweep at Subsonic, Transonic, and Supersonic Speeds

Description: Report discussing an investigation of the effect of spanwise aileron location on the rolling effectiveness of plain faired ailerons on untapered wing plan forms with designated sweep, airfoil sections, and aspect ratio using rocket-propelled test vehicles. Drag data is also presented for all configurations tested. Spanwise aileron location was found to have little effect on the effectiveness of the aileron on an unswept wing plan form.
Date: April 25, 1950
Creator: Strass, H. Kurt
Item Type: Refine your search to only Report
open access

Effect of Various Modifications on Drag and Longitudinal Stability and Control Characteristics at Transonic Speeds of a Model of the XF7U-1 Tailless Airplane: NACA Wing-FLow Method, TED No. NACA DE 307

Description: From Summary: "An investigation was made by the NACA wing-flow method to determine the drag, pitching-moment, lift, and angle-of-attack characteristics at transonic speeds of various configurations of a semispan model of an early configuration of the XF7U-1 tailless airplane. The results of the tests indicated that for the basic configuration with undeflected ailavator, the zero-lift drag rise occurred at a Mach number of about 0.85 and that about a five-fold increase in drag occurred through t… more
Date: April 20, 1950
Creator: Sawyer, Richard H. & Trant, James P., Jr.
Item Type: Refine your search to only Report
open access

Effect of wing-tank location on the drag and trim of a swept-wing model as measured in flight at transonic speeds

Description: Report presenting results of an exploratory free-flight investigation at zero lift of several rocket-powered drag research models equipped wing wing tanks at a range of Mach numbers. The tanks, which were slender bodies of revolution, were mounted on 34 degrees sweptback, nontapered wings of 2.7 aspect ratio. Results regarding drag and trim change are provided.
Date: April 4, 1950
Creator: Welsh, Clement J. & Morrow, John D.
Item Type: Refine your search to only Report
open access

Effect on longitudinal stability and control characteristics of a Boeing B-29 airplane of variations in stick-force and control-rate characteristics obtained through use of a booster in the elevator-control system

Description: A longitudinal stability and control characteristics of a Boeing B-29 airplane have been measured with a booster incorporated in the elevator-control system. Tests were made to determine the effects on the handling qualities of the test airplane of variations in the pilot's control-force gradients as well as the effects of variations in the maximum rate of control motion supplied by the booster. The results of the control-rate investigation indicate that large airplanes may have satisfactory ha… more
Date: April 12, 1950
Creator: Mathews, Charles W.; Talmage, Donald B. & Whitten, James B.
Item Type: Refine your search to only Report
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