UNT Libraries Government Documents Department - 13 Matching Results

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IBM Multigroup Numerical Procedures

Description: Introduction: "This paper presents in formula form IBM computational procedure for averaging cross-section data and for calculating reflected spherical reactors by the linear by the linear multigroup numerical method developed by the Physics Section of the ANP Central Design Group. The adjoint reactor numerical procedural is included."
Date: November 28, 1950
Creator: Holmes, David K. & Schulze, O. A.
Item Type: Refine your search to only Report
open access

Investigation of Blade-Row Flow Distributions in Axial-Flow-Compressor Stage Consisting of Guide Vanes and Rotor-Blade Row

Description: "A 30-inch tip-diameter axial-flow compressor stage was investigated with and without rotor to determine individual blade-row performance, interblade-row effects, and outer-wall boundary-layer conditions. Velocity gradients at guide-vane outlet without rotor approximated design assumptions, when the measured variation of leaving angle was considered. With rotor in operation, Mach number and rotor-blade effects changed flow distribution leaving guide vanes and invalidated design assumption of ra… more
Date: November 28, 1950
Creator: Mahoney, John J.; Dugan, Paul D.; Budinger, Raymond E. & Goelzer, H. Fred
Item Type: Refine your search to only Report
open access

Fundamental flame velocities of pure hydrocarbons 1: alkanes, alkenes, alkynes benzene, and cyclohexane

Description: The flame velocities of 37 pure hydrocarbons including normal and branched alkanes, alkenes, and alkynes; as well as benzene and cyclohexane, together with the experimental technique employed are presented. The normal alkanes have about the same flame velocity from ethane through heptane with methane being about 16 percent lower. Unsaturation increases the flame velocity in the order of alkanes, alkenes, and alkynes. Branching reduces the flame velocity.
Date: September 28, 1950
Creator: Gerstein, Melvin; Levine, Oscar & Wong, Edgar L.
Item Type: Refine your search to only Report
open access

Transonic Drag Characteristics of a Wing Body Combination Using a Thin Tapered Wing of 45 Degrees Sweepback

Description: Report presenting tests of a wing-body combination using the free-fall method, which was made up of a fineness-ratio-12 body with a 45 degree sweptback wing, an aspect ratio of 3.75, and an NACA 65-003 airfoil section in the direction perpendicular to the 50-percent-chord line. Results regarding the complete configuration, wing, body-tail combination, and component effects on total drag are provided.
Date: September 28, 1950
Creator: Kurbjun, Max C. & Faber, Stanley
Item Type: Refine your search to only Report
open access

Flight Measurements With the Douglas D-558-II (BuAero No. 37974) Research Airplane: Measurements of the Buffet Boundary and Peak Airplane Normal-Force Coefficients at Mach Numbers Up to 0.90

Description: Report presenting measurements of the buffet boundary and peak normal-force coefficients for the Douglas D-558-II airplane up to a Mach number of 0.90. Results regarding airplane lift curves and a comparison between the maximum normal-force coefficients and buffet boundaries for this particular aircraft and the Bell X-1 airplane are also provided.
Date: August 28, 1950
Creator: Mayer, John P. & Valentine, George M.
Item Type: Refine your search to only Report
open access

Examination of Masonite in Biological Shield : Interim Report

Description: Introduction: "Evidence of masonite deterioration in test hole plugs was interpreted to mean that a previous estimate of the minimum lifetime of the masonite in a Hanford biological shield might be somewhat optimistic. The importance of understanding the effects of radiations on masonite for both present and future pile shields dictated that masonite be sampled from an operating pile shield and studied. The results and techniques are discussed in the following sections of this report."
Date: June 28, 1950
Creator: Dickeman, R. L.
Item Type: Refine your search to only Report
open access

Free-Flight Performance of 16-Inch-Diameter Supersonic Ram-Jet Units 3: Four Units Designed for Combustion-Chamber-Inlet Mach Number of 0.245 at Free-Stream Mach Number of 1.8 (Units D-1, D-2, D-3, and D-4)

Description: Performance of four 16-inch-diameter ram-jet units was determined at free-stream Mach numbers of 0.49 to 1.78 over range of gas total-temperature ratios of 1.0 to 6.1. Time histories of each flight and data on thrust, drag, diffuser efficiency, and combustion are presented. A maximum thrust coefficient of 0.88 and a maximum net acceleration of 5.13 g's were observed for the four units.
Date: June 28, 1950
Creator: Disher, John H. & Rabinowitz, Leonard
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

Static Longitudinal Stability of a Tandem-Coupled Bomber-Fighter Airplane Configuration Similar to One Proposed by Douglas Aircraft Company, Inc.

Description: "At the request of the Air Materiel Command, an investigation was made in the Langley free-flight tunnel to determine the longitudinal stability and control characteristics of models coupled together in a tandem configuration for aerial refueling similar to one proposed by the Douglas Aircraft Company, Inc. Static force tests were made with 1/20-scale models of the B-29 and F-80 airplanes to determine the effects of rigidly coupling the airplanes together. The Douglas configuration differs from… more
Date: April 28, 1950
Creator: Hewes, Donald E.
Item Type: Refine your search to only Report
open access

Performance of High-Pressure-Ratio Axial-Flow Compressor Using Highly Cambered Naca 65-Series Blower Blades at High Mach Numbers

Description: "A complete stage of an axial-flow compressor was designed and built to investigate the possibility of obtaining a high pressure ratio with an acceptable efficiency through the use of the optimum combination of high blade loading and high relative inlet Mach number. Over-all stage performance was investigated over a range of flows at equivalent tip speeds of 418 to 836 feet per second. At design speed (836 ft/sec), a peak total-pressure ration of 1.445 was obtained with an adiabatic efficiency … more
Date: March 28, 1950
Creator: Voit, Charles H.; Guentert, Donald C. & Dugan, James F.
Item Type: Refine your search to only Report
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