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Rocket-Model Investigation to Determine the Hinge-Moment and Normal-Force Properties of a Full-Span, Constant-Chord, Partially Balanced Trailing-Edge Control on a 60 Degree Clipped Delta Wing Between Mach Numbers of 0.50 and 1.26

Description: Report presenting a free-flight investigation of a rocket-powered research model to determine the hinge-moment and normal-force characteristics of a trailing-edge control on a delta wing between Mach numbers of 0.50 and 1.26. The hinge-line location of 40 percent control chord satisfactorily reduced the high hinge moments associated with plain flap-type controls. Results regarding hinge moments and normal force are provided.
Date: October 30, 1953
Creator: Martz, C. William & Goslee, John W.
Partner: UNT Libraries Government Documents Department
open access

Determination of Rare Earths in Refined Uranium : Topical Report

Description: Abstract: "Rare-earth analyses were performed on several samples of refined uranium oxide and nitrate, using a modified cellulose column procedure. Rare earths were not detectable in samples of 0.03 shotgun of less. Detection limits were from 0.0005 to 0.015 ppm. Negligible quantities of low-cross-section rare earths were found in less pure uranium samples, obtained during start-up operations of the pilot plant at the Feed Materials Production Center, primarily those rare earths of greater than… more
Date: June 30, 1953
Creator: Ewing, R. A. & Bearse, A. E.
Partner: UNT Libraries Government Documents Department
open access

General Flattening and Power Curves

Description: Introduction: "In the evaluation of pile designs it is necessary to know how the production varies with the number of tubes. It has been possible to solve the problem in terms of some general parameters whose values may be quickly computed for any specific design when the pertinent information is available."
Date: March 30, 1953
Creator: Gast, Paul F.
Partner: UNT Libraries Government Documents Department
open access

Recent Developments in Powder Metallurgy

Description: Brief notes from a meeting between NAA and S. B. Roboff, Sylvania Electric Products, regarding the important developments in powder metallurgy fuels and reactor materials.
Date: June 30, 1953
Creator: Hayward, B.R.
Partner: UNT Libraries Government Documents Department
open access

Proton-Proton Scattering at 9.7 Mev

Description: No Description Available.
Date: October 30, 1953
Creator: Cork, B. & Hartsough, W.
Partner: UNT Libraries Government Documents Department
open access

Experimental and theoretical investigation of rotating-stall characteristics of single-stage axial-flow compressor with hub-tip ratio of 0.76

Description: Report presenting the overall performance and rotating stall characteristics of a single-stage compressor with a hub-tip ratio of 0.76 and a symmetrical velocity diagram over a wide range of weight flow for several different design speed percentages. No discontinuities in performance were noted at an operating condition. Results regarding the overall performance, types of rotating stall observed, circumferential extent of stall zones, flow fluctuations incited by rotating stall, rotating-stall … more
Date: November 30, 1953
Creator: Graham, Robert W. & Prian, Vasily D.
Partner: UNT Libraries Government Documents Department
open access

Preliminary investigation of the effects of several seeker-nose configurations on the longitudinal characteristics of a canard-type missile at a Mach number of 1.60

Description: Report presenting an investigation to determine the effect of several seeker-nose configurations on the static longitudinal stability, canard control characteristics, and lift and drag at Mach number 1.60 of a canard-type ramjet missile with 70 degree delta canard control surfaces and 70 degree delta wings. The tests indicate that, for the most part, the configurations tested exhibited no significant difference in static longitudinal stability or horizontal-canard control effectiveness.
Date: October 30, 1953
Creator: Robins, A. Warner
Partner: UNT Libraries Government Documents Department
open access

Performance of a swept leading edge rotor of the supersonic type with mixed flow

Description: Report investigation Freon-12 as the working fluid for a 14-inch-diameter supersonic mixed-flow axial-discharge rotor of the impulse type. The whole series of tests was performed twice, once with guide vanes that underturned the air and gave a lower relative inlet velocity and once with a set that gave the design values for velocity and direction. Results regarding the overall performance characteristics, entrance flow, internal pressure patterns, exit flow, and rotor losses are provided.
Date: January 30, 1953
Creator: Goldstein, Arthur W. & Schacht, Ralph L.
Partner: UNT Libraries Government Documents Department
open access

Preliminary Investigation of a Chemical Starting Technique for the Acid - Gasoline Rocket Propellant System

Description: Memorandum presenting an investigation of the use of a small quantity of fluid that ignites spontaneously within nitric acid to initiate the acid-gasoline reaction carried out in a 200-pound-thrust uncooled engine with a characteristic length of 30 inches at a range of temperatures. The starting process was divided into two phases: ignition and transition. Results regarding ignition temperature limits, effect of temperature on allowable igniter fuel flow, optimum valve opening time for ignition… more
Date: January 30, 1953
Creator: Hennings, Glen & Morrell, Gerald
Partner: UNT Libraries Government Documents Department
open access

Force and pressure recovery characteristics at supersonic speeds of a conical spike inlet with bypasses discharging in an axial direction

Description: Report presenting an investigation of an axially symmetric nacelle-type conical spike inlet with two bypasses located in the horizontal plane and on opposite sides of the nacelle in the 8- by 6-foot supersonic tunnel at several Mach numbers and angles of attack. Results regarding the performance with open bypasses and with closed bypasses are provided.
Date: January 30, 1953
Creator: Allen, J. L. & Beke, Andrew
Partner: UNT Libraries Government Documents Department
open access

Evaluation of effects of random permeability variations on transpiration-cooled surfaces

Description: Report presenting an analytical investigation to evaluate the effects of permeability variations on surface temperatures and coolant flows for ranges of temperature and Reynolds number that are of particular interest for gas-turbine blades. Results regarding small-orifice calibrations, effect of orifices in series with porous surfaces on permeability correlation, effect of permeability variations on coolant-flow rates and porous-wall temperatures, evaluation of the experimental porous blade, an… more
Date: November 30, 1953
Creator: Esgar, Jack B. & Richards, Hadley T.
Partner: UNT Libraries Government Documents Department
open access

Comparison of theoretically and experimentally determined effects of oxide coatings supplied by fuel additives on uncooled turbine-blade temperature during transient turbojet-engine operation

Description: From Summary: "An analysis was made to permit the calculation of the effectiveness of oxide coatings in retarding the transient heat flow into turbine blades when the combustion gas temperature of a turbojet engine is suddenly changed. The analysis is checked with experimental data obtained from a turbojet engine whose blades were coated with two different coating materials (silicon dioxide and boric oxide) by adding silicone oil and tributyl borate to the engine fuel. The very thin coatings (a… more
Date: March 30, 1953
Creator: Schafer, Louis J., Jr.; Stepka, Francis S. & Brown, W. Byron
Partner: UNT Libraries Government Documents Department
open access

Preliminary flight measurements of the dynamic longitudinal stability characteristics of the Convair XF-92A delta-wing airplane

Description: Report presenting an analysis of some longitudinal maneuvers obtained during performance tests of the Convair XF-92A by using measured period and time to damp to half amplitude and with a computer to give a preliminary measurement of the airplane stability and damping at a range of Mach numbers. Results indicated that no loss in control effectiveness was shown, the static stability increased with Mach number, the damping was light but positive, and the damping factor was low.
Date: June 30, 1953
Creator: Holleman, Euclid C.; Evans, John H. & Triplett, William C.
Partner: UNT Libraries Government Documents Department
open access

Wind-tunnel investigation of the aerodynamic characteristics in pitch of wing-fuselage combinations at high subsonic speeds: taper-ratio series

Description: Report presenting a continuation of the program in the high-speed 7- by 10-foot tunnel to investigate the aerodynamic characteristics in pitch, sideslip, and steady roll of model configurations with variations in wing geometric parameters. This report contains the aerodynamic characteristics in pitch of wing-fuselage combinations with wings of aspect ratio 4, sweepback angle of 45 degrees, and three different taper ratios. Results regarding lift characteristics, pitching-moment characteristics,… more
Date: June 30, 1953
Creator: King, Thomas J., Jr. & Pasteur, Thomas B., Jr.
Partner: UNT Libraries Government Documents Department
open access

Characteristics of a canard-type missile configuration with an underslung scoop inlet at Mach numbers from 1.5 to 2.0

Description: Report presenting an experimental investigation of a canard-type missile configuration with an underslung scoop inlet in the 8 by 6-foot supersonic wind tunnel at a range of Mach numbers, angles of attack, control-surface deflection angles, boundary-layer-scoop heights, and inlet mass-flow ratios. Measurement of the external forces indicated that maximum lift-drag ratios were in excess of 5 at all test Mach numbers.
Date: January 30, 1953
Creator: Fradenburgh, Evan A. & Campbell, Robert C.
Partner: UNT Libraries Government Documents Department
open access

Investigation of an Axial-Flow Compressor Rotor Having Naca High-Speed Blade Sections (A(Sub 2)I(Sub 8B) Series) at Mean Radius Relative Inlet Mach Numbers Up to 1.13

Description: Report presenting the results of testing on a high-pressure-ratio, axial-flow compressor rotor designed to operate efficiently at high speeds. High flows are needed to increase engine thrust without increasing engine front area. Results regarding the overall total-pressure ratio and adiabatic efficiency, effect of angle of attack on efficiency, determination of the effect of mean radius rotor inlet Mach number and Reynolds number on turning angle, and other information about ideal operation of … more
Date: November 30, 1953
Creator: Savage, Melvyn; Erwin, John R. & Whitley, Robert P.
Partner: UNT Libraries Government Documents Department
open access

Wake Surveys in the Slipstream of a Full-Scale Supersonic-Type Three-Blade Propeller at Mach Numbers to 0.96

Description: Report presenting an investigation of the thrust loading by wake surveys in the slipstream of a full-scale supersonic-type three-blade propeller (the Curtiss-Wright 109622) that was conducted in the transonic tunnel. Integrated-thrust coefficient values were found to be in good agreement with the force data. Results regarding thrust loading at constant advance ratios, at advance ratios for maximum efficiency, and lift-coefficient distribution are also provided.
Date: October 30, 1953
Creator: Swihart, John M. & Norton, Harry T., Jr.
Partner: UNT Libraries Government Documents Department
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