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Events of importance for week ending November 30, 1949

Description: Waste disposal, pile operations and P-10 operations are reported. Construction in the 100 (Pile) areas, 200 (Separations) areas, and 400 (Technical Center) area is described. General work included Richland paving, the Southern Railroad connection, and the Richland levee. Personnel data and visitor information is also included.
Date: December 2, 1949
Creator: Schlemmer, F. C.
Item Type: Refine your search to only Report
open access

Survey of two-dimensional data on pitching-moment changes near maximum lift caused by deflection of high-lift devices

Description: Report presenting a survey of two-dimensional data on trim changes near maximum lift resulting from deflection of various types of leading-edge and trialing-edge high lift devices. Results regarding pitching-moment coefficients, pitching-moment increments, and maximum lift coefficients are provided.
Date: December 2, 1949
Creator: Bidwell, Jerold M. & Cahill, Jones F.
Item Type: Refine your search to only Report
open access

The Determination of Uranium by Potentiometric Titration with Ferric Sulfate

Description: Abstract: "A method for the potentiometric titration of uranium with ferric sulfate is described. This method provides a rapid and accurate way of determining the element in solutions free from interfering ions. Application of the method to analysis of pure uranium compounds and to uranium recovered from contaminated solutions by suitable procedures is briefly discussed."
Date: November 2, 1949
Creator: Grimes, W. R.
Item Type: Refine your search to only Report
open access

Tests of Lifting Surfaces on Conical and Cylindrical Portions of a Body at Subsonic Mach Numbers and at a Mach Number of 1.2

Description: Report presenting testing of low-aspect-ratio triangular-plan-form lifting surfaces located on conical and cylindrical portions of a body have been determined at Mach number 1.2 and several subsonic speeds to determine if the aerodynamic characteristics of these surfaces at supersonic speeds could be improved by locating them in the subsonic conical-flow field. Results regarding lift and drag coefficients and lift-curve slopes are provided.
Date: September 2, 1949
Creator: Osborne, Robert S. & Wright, John B.
Item Type: Refine your search to only Report
open access

Theoretical analysis of various thrust-augmentation cycles for turbojet engines

Description: "The results of analytical studies of tail-pipe-burning, water-injection, and bleedoff methods of thrust augmentation are presented that provide an insight into the operating characteristics of these augmentation methods and summarizes the performance that may be obtained when applied to a typical turbojet engine. A brief description of the principles of operation of each augmentation method is given, together with curves that illustrate the effects of the principal design and operating variabl… more
Date: September 2, 1949
Creator: Lundin, Bruce T.
Item Type: Refine your search to only Report
open access

Altitude-Test-Chamber Investigation of McDonnell Afterburner on J34 Engine

Description: "An altitude-test-chamber investigation was conducted to determine the operational and performance characteristics of a McDonnell afterburner with a fixed-area exhaust nozzle on a J34 engine. At rated engine speed, the altitude limit, as determined by combustion blow-out, occurred as a band of unstable operation of about 6000-foot altitude in width with minimum altitude limits from 31,000 feet at a simulated flight Mach number of 0.40 to about 45,500 feet at a simulated flight Mach number of 1.… more
Date: June 2, 1949
Creator: Reller, John O. & Dowman, Harry W.
Item Type: Refine your search to only Report
open access

Comparison of performance of AN-F-58 and AN-F-32 fuels in J33-A-23 turbojet engine

Description: Report presenting an investigation using a 4600 pound-thrust turbojet engine as part of a program to determine the comparative performance of fuels conforming to specifications AN-F-58 and AN-F-32. Results regarding the altitude performance, altitude low-speed blow-out limits, idling limits of fuel-metering control, altitude windmilling starts, carbon-deposition rates, and iron oxide contamination are provided.
Date: June 2, 1949
Creator: Wilsted, H. D. & Armstrong, J. C.
Item Type: Refine your search to only Report
open access

Flight Investigation of the Jettisonable-Nose Method of Pilot Escape Using Rocket-Propelled Models

Description: Report discussing testing using two rocket-propelled models to test the jettisonable-nose method of pilot escape. The nose was jettisoned successfully on the second attempt and the accelerations produced were found to be within human tolerance. The first test ended with a collision of the nose and wing, indicating that this is a possible risk during power-on flight.
Date: June 2, 1949
Creator: Lundstrom, Reginald R. & O'Kelly, Burke R.
Item Type: Refine your search to only Report
open access

Altitude-wind-tunnel investigation of AN-F-58 fuel in experimental version of J47 turbojet engine

Description: An altitude-wind-tunnel investigation of the performance of AN-F-58 and AN-F-32 fuels in an experimental turbojet engine was conducted over a range of simulated altitudes and flight Mach numbers. Combustion efficiencies obtained with AN-F-58 and AN-F-32 fuels were approximately equal. The minimum-speed altitude operational limit was essentially the same with either AN-F-58 or AN-F-32 fuel. Starting characteristics of the two fuels were approximately the same at low wind milling speeds. Visual o… more
Date: May 2, 1949
Creator: Meyer, Carl L.
Item Type: Refine your search to only Report
open access

An Approximate Method for Estimating the Incompressible Laminar Boundary-Layer Characteristics on a Flat Plate in Slipping Flow

Description: Memorandum presenting an approximate method for the estimation of the properties of the incompressible laminar boundary layer on a flat plate in the slip-flow region using Karman's momentum method. At equivalent stations, the total thickness and the skin friction of a slipping boundary layer are less than that of the normal boundary layer at the same Reynolds number.
Date: May 2, 1949
Creator: Donaldson, Coleman duP.
Item Type: Refine your search to only Report
open access

A high-speed low-sensitivity calorimeter for high activity (Ad Interim Report)

Description: This document is a March 1949 Ad Interim Report on the development of a high-speed, low-sensitivity calorimeter at the Mound Laboratory. This calorimeter is a zero-compensating, thermocouple, twin type. The outside diameter of the aluminum tubing was machined for a slip fit into the glass test tube. Prior to assembling in the test tube, an aluminum plug was pressed in it midway from the ends. A groove was also milled on the outside down to the plug, and a copper-constantan thermocouple was secu… more
Date: March 2, 1949
Creator: Haring, M. M.
Item Type: Refine your search to only Report
open access

Investigation of the Effect of Tip Tanks on the Wing Loading of a Republic F-84 Airplane in the Ames 40- by 80-foot Wind Tunnel

Description: Wind-tunnel tests at low Mach number of a Republic F-84C airplane were conducted to determine by pressure-distribution measurements the air loads on wing-tip tanks and the change in wing load distribution due to the presence of tip tanks. Measurements of the aeroelastic twist of the wing were also obtained. Results are presented in the form of loading coefficient, center-of- pressure location, pitching-moment coefficient, aerodynamic-center location, and aeroelastic twist. The investigation rev… more
Date: February 2, 1949
Creator: Hunton, Lynn W.; Dew, Joseph K. & Salisbury, Ralph D.
Item Type: Refine your search to only Report
open access

Flight Investigation to Determine the Aerodynamic Characteristics of Rocket-Powered Models Representative of a Fighter-Type Airplane Configuration Incorporating an Inverse-Taper Wing and a Vee Tail

Description: From Summary: "Two rocket-powered models representative of a fighter-type airplane were investigated in flight at Mach numbers up to 1.01 and 1.07 by the Langley Pilotless Aircraft Research Division at its testing station at Wallops Island, Va. These models incorporated an inverse-taper wing and a vee tail and were flown with controls undeflected and wing and stabilizer set at 0 deg incidence. Values of lateral acceleration, normal acceleration velocity, and drag were obtained by use of telemet… more
Date: November 2, 1948
Creator: Alexander, Sidney R.
Item Type: Refine your search to only Report
open access

Wind-Tunnel Investigation of High-Lift and Stall-Control Devices on a 37 Degree Sweptback Wing of Aspect Ratio 6 at High Reynolds Numbers

Description: "Results are presented of an investigation in the Langley 19-foot pressure tunnel of the longitudinal characteristics of a semispan model wing having 37 degrees sweepback of the leading edge, an aspect ratio of 6, and NACA 641-212 airfoil section perpendicular to the 27-percent-chord line. Several types of stall-control devices including extensible round-nose leading-edge flaps, a leading-edge slat, and a drooped leading edge were investigated; partial- and full-span trailing-edge split and dou… more
Date: September 2, 1948
Creator: Koven, William & Graham, Robert R.
Item Type: Refine your search to only Report
open access

Preliminary Results of an Altitude-Wind-Tunnel Investigation of an Axial-Flow Gas Turbine-Propeller Engine 1 - Performance Characteristics

Description: A preliminary investigation of an axial-flow gas turbine-propeller engine was conducted. Performance data were obtained for engine speeds from 8000 to 13,000 rpm and altitudes from 5000 to 35,000 feet and compressor inlet ram pressure ratios from 1.00 to 1.17.
Date: August 2, 1948
Creator: Saari, Martin J. & Wallner, Lewis E.
Item Type: Refine your search to only Report
open access

Preliminary Results of an Altitude-Wind-Tunnel Investigation of an Axial-Flow Gas Turbine-Propeller Engine 2 - Windmilling Characteristics

Description: Performance properties and operational characteristics of an axial-flow gas turbine-propeller engine were determined. Data are presented for a range of simulated altitudes from 5,000 to 35,0000 feet, compressor inlet- ram pressure ratios from 1.00 to 1.17, and engine speeds from 8000 to 13,000 rpm.
Date: August 2, 1948
Creator: Geisenheyner, Robert M. & Berdysz, Joseph J.
Item Type: Refine your search to only Report
open access

Analysis of Performance of Jet Engine From Characteristics of Components 2: Interaction of Components as Determined From Engine Operation

Description: "In order to understand the operation and the interaction of jet-engine components during engine operation and to determine how component characteristics may be used to compute engine performance, a method to analyze and to estimate performance of such engines was devised and applied to the study of the characteristics of a research turbojet engine built for this investigation. An attempt was made to correlate turbine performance obtained from engine experiments with that obtained by the simple… more
Date: June 2, 1948
Creator: Goldstein, Arthur W.; Alpert, Sumner; Beede, William & Kovach, Karl
Item Type: Refine your search to only Report
open access

Investigation of a Thin Wing of Aspect Ratio 4 in the Ames 12-Foot Pressure Wind Tunnel 1: Characteristics of a Plain Wing

Description: Memorandum presenting wind-tunnel tests of a semispan model of an unswept wing of aspect ratio 4 and taper ratio 0.5 at Mach numbers up to 0.94 to determine its aerodynamic characteristics as influenced by Mach number, Reynolds number, and modification of the basic diamond profile by rounding the ridge. Lift, drag, and pitching-moment data are presented for a range of Reynolds and Mach numbers. The results indicated that no severe static-longitudinal-stability problems up to Mach number 0.94.
Date: June 2, 1948
Creator: Johnson, Ben H., Jr.
Item Type: Refine your search to only Report
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