UNT Libraries Government Documents Department - 23 Matching Results

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Analysis of Wind-Tunnel Tests at Low Speeds of a Four-Engine Propeller-Driven Airplane Configuration Having a Wing With 40 Degrees of Sweepback

Description: Report presenting an investigation to determine the effects of operating propellers on the longitudinal characteristics of a four-engine tractor airplane with a 40 degree swept wing with an aspect ratio of 10. Results regarding components of the lift changes due to operating propellers, components of the pitching-moment changes due to operating propellers, effect of configuration changes on the pitching-moment characteristics of the model, stick-fixed longitudinal stability of the model, reduct… more
Date: October 8, 1954
Creator: Edwards, George G. & Buell, Donald A.
Item Type: Refine your search to only Report
open access

The Effect of Magnesium Particles of Various Equivalent Diameters on Some Physical Properties of Petrolatum-Stabilized Magnesium-Hydrocarbon Slurries

Description: Memorandum presenting the effect of magnesium particles of various equivalent diameters on the apparent viscosity, sedimentation ratio, and redispresibility of petroleum-stabilized magnesium-JP-4 slurries. Powders of the following equivalent diameters were investigated: 2.8, 3.8, 7.2, 9.3, 12.0, and 14.8 microns. An analysis of the experimental error and reproducibility of values of apparent viscosity, sedimentation ratio, and redispersibility of the slurries was also made.
Date: April 8, 1954
Creator: Lamberti, Joseph M.
Item Type: Refine your search to only Report
open access

Effect of Wing Slats and Inboard Wing Fences on the Longitudinal Stability Characteristics of the Douglas D-558-II Airplane in Accelerated Maneuvers at Subsonic and Transonic Speeds

Description: Memorandum presenting testing of a D-558-II airplane with the wing slats fully extended, with and without inboard wing fences, and with the wing slats half extended and wing fences removed. In order to improve the stick-force characteristics at moderate and large angles of attack, additional tests were conducted with two bungees of differing stiffness alternately attached to the control column.
Date: February 8, 1954
Creator: Fischel, Jack
Item Type: Refine your search to only Report
open access

Effects of sweep and thickness on the static longitudinal aerodynamic characteristics of a series of thin, low-aspect-ratio, highly tapered wings at transonic speeds: transonic-bump method

Description: An investigation by the transonic-bump technique of the static longitudinal aerodynamic characteristics of a series of thin, low-aspect-ratio, highly tapered wings has been made in the Langley high-speed 7- by 10-foot tunnel. The Mach number range extended from about 0.60 to 1.18, with corresponding Reynolds numbers ranging from about 0.75 x 10(6) to 0.95 x 10(6). The angle of attack range was from -10 degrees to approximately 32 degrees.
Date: April 8, 1954
Creator: Few, Albert G., Jr. & Fournier, Paul G.
Item Type: Refine your search to only Report
open access

Experimental Investigation of a Five-Stage Axial-Flow Research Compressor with Transonic Rotors in All Stages 1: Compressor Design

Description: Memorandum presenting a five-stage axial-flow compressor with all rotor rows operating with transonic relative inlet Mach numbers designed as a research unit to study the potentialities and problems arising from the compounding of transonic stages. The report presents all design values and procedures, blade-row velocity diagrams, and the selection of blade shapes.
Date: September 8, 1954
Creator: Sandercock, Donald M.; Kovach, Karl & Lieblein, Seymour
Item Type: Refine your search to only Report
open access

Experimental Investigation of a Five-Stage Axial-Flow Research Compressor With Transonic Rotors in All Stages 2: Compressor Over-All Performance

Description: Memorandum presenting an evaluation of the overall performance of a 20-inch-diameter five-stage compressor as the initial step in an investigation of the potential performance and problems associated with a high-stage-pressure ratio compressor. The overall performance was evaluated over a range of flows at equivalent tip speeds from 40 to 100 percent of design. Results regarding the overall performance, compressor-inlet conditions, compressor-discharge conditions, stagewise variation of static … more
Date: September 8, 1954
Creator: Kovach, Karl & Sandercock, Donald M.
Item Type: Refine your search to only Report
open access

Free-Flight Tests of 1/9-Scale Convair YF-102 Airplane Wings at Transonic and Supersonic Speeds to Investigate the Possibility of Flutter

Description: "Free-flight tests in the transonic and supersonic speed ranges utilizing rocket-propelled models have been made on two pairs of 1/9-scale Convair YF-102 airplane wings with elevons to investigate the possibility of flutter . These wings had modified 60 deg delta plan forms with the trailing edge swept forward 5 deg. The aspect ratio of two exposed wing panels was 2.19 and the wings had NACA 0004-65 (modified) airfoil sections. The model wings and elevons were dynamic-scale models at sea level … more
Date: December 8, 1954
Creator: O'Kelly, Burke R.
Item Type: Refine your search to only Report
open access

Hydrodynamic Investigation of the the Take-Off Characteristics of a 1/10-Scale Dynamic Model of the Convair XF2Y-1 Airplane

Description: "An investigation was made of the take-off characteristics of a 1/10-scale dynamic model of the Convair XF2Y-1 airplane. This airplane is a water-based, jet-propelled, delta-wing fighter incorporating a hydro-ski landing gear. Tests were made with the original configuration, with the beaching wheels removed, and with the wheels installed and fairings added in front of the wheels" (p. 1).
Date: July 8, 1954
Creator: McBride, Ellis E. & Fisher, Lloyd J.
Item Type: Refine your search to only Report
open access

Investigation of a Pulse-Jet-Powered Helicopter Rotor on the Langley Helicopter Test Tower

Description: Report discussing testing of a helicopter rotor powered by pulse-jet engines located at the rotor-blade tips. The basic hovering characteristics of the rotor and propulsive characteristics of the pulse-jet engine were obtained at a range of engine speeds with the engines rigidly fixed to the blade tips and with the engines free to pivot. Measurements were also taken to determine the effect of inlet blockage on the power-off drag of the jet engines and the noise intensity in the vicinity of oper… more
Date: February 8, 1954
Creator: Radin, Edward J. & Carpenter, Paul J.
Item Type: Refine your search to only Report
open access

Investigation of the NACA 4-(5)(05)-037 six- and eight-blade, dual-rotation propellers at positive and negative thrust at Mach numbers up to 0.90, including some aerodynamic characteristics of the NACA 4-(5)(05)-041 two- and four-blade, single-rotat

Description: Report presenting an investigation to determine the aerodynamic characteristics of the NACA 4-(5)(05)-037 six- and eight-blade, dual-rotation propellers operating at positive and negative thrust at a range of Mach numbers when operating at near static conditions. The propellers were operated in combination with a long spinner and at a variety of blade angles.
Date: October 8, 1954
Creator: Walker, John H. & Reynolds, Robert M.
Item Type: Refine your search to only Report
open access

MTA Progress Report for June through November, 1953

Description: Introduction: "This report covers the contributions of UCRL to MTA research and development program during the period June 1 to November 30, 1953. In this program UCRL continues to work in close collaboration with the California Research and Development Company (CRD)."
Date: February 8, 1954
Creator: Lawrence Radiation Laboratory
Item Type: Refine your search to only Report
open access

Pressure Recovery and Drag Characteristics of a Forward Located Circular Scoop Inlet as Determined From Flight Tests for Mach Numbers From 0.8 to 1.6

Description: Report presenting testing of a circular scoop inlet located far forward on a parabolic body of revolution at a range of Mach and Reynolds numbers and mass-flow ratios. The inlet had an area equal to 8 percent of the body frontal area. Results regarding total and base drag coefficients, external drag coefficients, and inlet total-pressure recovery are provided.
Date: April 8, 1954
Creator: Merlet, Charles F.
Item Type: Refine your search to only Report
open access

Probability of ruthenium reduction in H-4 by self-radiation

Description: The following calculations have been made at the request of H.R. Schmidt to determine the probability that self-radiation may play a substantial role in the decomposition of the ruthenium tetroxide in the reflux scrubber, section of the Redox Ruthenium Oxidizer (H-4). The validity of the derived data necessarily depends upon the correctness of the basic assumptions made with regard to process conditions and to possible radiation-activated mechanisms of disintegration. It is estimated that the e… more
Date: June 8, 1954
Creator: Upson, U. L.
Item Type: Refine your search to only Report
open access

Pumping Characteristics for Several Simulated Variable-Geometry Ejectors With Hot and Cold Primary Flow

Description: Report presenting an investigation of the pumping characteristics of eight conical ejectors mounted on a fuselage portion of a supersonic airplane. The diameter ratio, spacing ratio, nozzle pressure, and ejector weight flows were varied. Results regarding the ejector pumping characteristics, comparison with previous results, comparison of data for cold and hot primary flow, and ejector air-supply requirements are provided.
Date: September 8, 1954
Creator: Allen, John L.
Item Type: Refine your search to only Report
open access

Pumping Characteristics for Several Simulated Variablegeometry Ejectors With Hot and Cold Primary Flow

Description: Report presenting an investigation of the pumping characteristics of eight conical ejectors mounted on a scale fuselage portion of a supersonic airplane. The configurations simulated various positions of a two-position nozzle with a fixed shroud and double-iris exit. Results regarding ejector pumping characteristics, comparison with previous results, comparison of data for cold and hot primary flow, and ejector air-supply requirements are provided.
Date: September 8, 1954
Creator: Allen, John L.
Item Type: Refine your search to only Report
open access

A Summary of Preliminary Investigations Into the Characteristics of Combustion Screech in Ducted Burners

Description: "Increasing demands for higher afterburner performance have required operation at progressively higher fuel-air ratios, which has increased the occurrence and intensity of screeching combustion. The onset of screech may be followed by rapid destruction of the combustor shell and other combustor parts. Because of its destructive characteristics, considerable effort has been expended to understand and eliminate screech. NACA work on the screeching combustion problem prior to 1954 is summarized he… more
Date: February 8, 1954
Creator: Lewis Laboratory Staff
Item Type: Refine your search to only Report
open access

TBP plant nickel ferrocyanide scavenging flowsheet

Description: Recent plant-scale scavenging and cribbing tests have confirmed laboratory data which indicated that the cesium and strontium in TBP wastes could be reduced by nickel ferrocyanide scavenging to concentrations which permit discharge of the scavenged supernatant to cribs. In this document a chemical flowsheet is presented for use as a design basis for facilities which will permit scavenging of unconcentrated neutralized waste for the TBP Plant.
Date: January 8, 1954
Creator: Sloat, R. J.
Item Type: Refine your search to only Report
open access

A Transonic Wind-Tunnel Investigation of the Longitudinal Aerodynamic Characteristics of a Model of the Lockheed XF-104 Airplane

Description: "The transonic longitudinal aerodynamic characteristics of a 0.0858-scale model of the Lockheed XF-104 airplane have been obtained from tests at the Langley 16-foot transonic tunnel. The results of the investigation provide some general information applicable to the transonic properties of thin, low-aspect-ratio, unswept wing configurations utilizing a high horizontal tail . The model employs a horizontal tail mounted at the top of the vertical tail and a wing with an aspect ratio of 2.5, a tap… more
Date: November 8, 1954
Creator: Hieser, Gerald & Reid, Charles F., Jr.
Item Type: Refine your search to only Report
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