Resource Type
Serial/Series Title
NACA Research Memorandums
141
Atomic Energy Commission Reports
35
Hanford Works Reports
17
HW (Series)
14
Oak Ridge National Laboratory Reports
14
University of California Radiation Laboratory Reports
11
NACA Technical Reports
8
ORNL (Series)
7
AEC research and development report
5
AECU (Series)
5
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Pressure Distributions on the Blade Sections of the NACA 10-(3)(066)-033 Propeller Under Operating Conditions
The first report in a series of five that present unanalyzed pressure data obtained in tests of five full-scale propellers with NACA 16-series blade sections. Pressure distributions on the blade sections were measured under operating conditions to determine the aerodynamic characteristics of each blade section. This particular report presents information for eleven radial stations of the NACA 10-(3)(066)-033 propeller.
Date:
January 24, 1950
Creator:
Maynard, Julian D. & Murphy, Maurice P.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic characteristics of a wing with quarter-chord line swept back 60 degrees, aspect ratio 2, taper ratio 0.6, and NACA 65A006 airfoil section : transonic bump method
From Introduction: "This paper presents the results of the investigation of the wing-alone and wing-fuselage configurations employing a wing with the quarter-chord line swept back 60^o, aspect ratio 2, taper ratio 0.6, and an NACA 65A006 airfoil section parallel to the free stream."
Date:
February 24, 1950
Creator:
Myers, Boyd C., II & King, Thomas J., Jr.
Object Type:
Report
System:
The UNT Digital Library
Determination of Minimum Moments of Inertia of Arbitrarily Shaped Areas, Such as Hollow Turbine Blades
Memorandum presenting a method for approximately determining the minimum moment of inertia of an arbitrarily shaped area, such as the section of a hollow turbine blade. The practical application of the method involves a simple routine tabular procedure.
Date:
February 24, 1950
Creator:
Gendler, Sel & Johnson, Donald F.
Object Type:
Report
System:
The UNT Digital Library
Investigation of frequency-response characteristics of engine speed for a typical turbine-propeller engine
Experimental frequency-response characteristics of engine speed for a typical turbine-propeller engine are presented. These data were obtained by subjecting the engine to sinusoidal variations of fuel flow and propeller-blade-angle inputs. Correlation is made between these experimental data and analytical frequency-response characteristics obtained from a linear differential equation derived from steady-state torque-speed relations.
Date:
March 24, 1950
Creator:
Taylor, Burt L., III & Oppenheimer, Frank L.
Object Type:
Report
System:
The UNT Digital Library
Investigation of High-Subsonic Performance Characteristics of a 12 Degree 21-Inch Conical Diffuser, Including the Effects of Change in Inlet-Boundary-Layer Thickness
"Investigations were conducted of a 12 degree 21-inch conical diffuser of 2:1 area ratio to determine the interrelation of boundary layer growth and performance characteristics. Surveys were made of inlet and exit from, longitudinal static pressures were recorded, and velocity profiles were obtained through an inlet Reynolds number range, determined from mass flows and based on inlet diameter of 1.45 x 10(exp 6) to 7.45 x 10(exp 6) and a Mach number range of 0.11 to approximately choking. These investigations were made to two thicknesses of inlet boundary layer" (p. 1).
Date:
March 24, 1950
Creator:
Copp, Martin R. & Klevatt, Paul L.
Object Type:
Report
System:
The UNT Digital Library
Solubility relationships of acidified stored metal wastes
The reports aims to determine the solubility limitation of concentrations of uranium in the food preparation step of the tributyl phosphate waste metal recovery process, and the subsequent solubilities in the RA column.
Date:
March 24, 1950
Creator:
Curtis, M. H.
Object Type:
Report
System:
The UNT Digital Library
An improved approximate method for calculating lift distributions due to twist
Report presenting a method for calculating the lift distribution due to twist which gives a closer approximation than the current Schrenk empirical method and requires about the same amount of computing. The method uses the lifting-line theory and makes use of the lift distribution due to angle of attack and considers the aspect ratio of the wing. Examples are presented for four main types of twist: symmetrical, antisymmetrical, continuous, and discontinuous.
Date:
May 24, 1950
Creator:
Sivells, James C.
Object Type:
Report
System:
The UNT Digital Library
Damping in Roll of Rectangular Wings of Several Aspect Ratios and Naca 65a-Series Airfoil Sections of Several Thickness Ratios at Transonic and Supersonic Speeds as Determined With Rocket-Powered Models
Report presenting rocket-powered flight tests to determine the damping in roll of rectangular wings of various aspect ratios and thickness ratios using NACA airfoil sections. The experimental damping in roll was consistently lower than what was predicted theoretically.
Date:
August 24, 1950
Creator:
Edmondson, James L.
Object Type:
Report
System:
The UNT Digital Library
Effect of Retractable Ignition Plug on Plug Fouling by Carbon Deposits
Memorandum presenting an investigation conducted using a single combustor from a 4600-pound-thrust turbojet engine to determine if ignition-plug fouling by carbon deposits could be prevented by retracting the plug from the combustion zone during operation after ignition had taken place. The fuels used were normally conducive to forming carbon. The results indicated that retracting the ignition plug from the combustion zone after ignition prevented plug fouling by carbon.
Date:
August 24, 1950
Creator:
Wear, Jerrold D. & Locke, Theodore E.
Object Type:
Report
System:
The UNT Digital Library
Interpretation of boundary-layer pressure-rake data in flow with a detached shock
From Summary: "A procedure is presented for determining boundary-layer quantities from pressure-rake data, which include the combined effects of viscous and shock losses. The problem is analyzed using schileren photographs of the shock configuration, the continuity of mass relationship, and the characteristics of the turbulent boundary layer that its outer edge is defined by a rapid change in slope in the Mach-number profiles in the vicinity of the edge."
Date:
August 24, 1950
Creator:
Luidens, Roger W. & Madden, Robert T.
Object Type:
Report
System:
The UNT Digital Library
The Photoproduction of Mesons from Hydrogen
In an effort to gain information on the nature of the photon-meson and photon-nucleon interaction, a study of the artificial production of mesons by photons has been made at the Berkeley synchrotron. The major effort of this research was concentrated on a measurement of the energy and angular distribution of u+-mesons produced when the photons strike a target of liquid hydrogen. Detection of the mesons is accomplished electronically by the technique of delayed coincidence.
Date:
August 24, 1950
Creator:
Bishop, Amasa Stone
Object Type:
Report
System:
The UNT Digital Library
Heat of Reaction of Chlorine Trifluoride with Water
Abstract: "A measurement of the heat liberated when chlorine trifluoride reacts with water has been made in a simple Dewar calorimeter. The chlorine trifluoride vapor was bubbled into approximately 20 moles of water; the weight of material used, heat equivalent of the calorimeter, and the temperature rise of the water and calorimeter were determined. From these data an average value for the heat of reaction was calculated to be 81.0 +/- 0.4 kcal/mole. Analysis of the reaction solution and evolved gas showed the following to be present: hydrogen fluoride, hydrogen chloride, chlorine, oxygen, and probably oxygen-chlorine compounds."
Date:
October 24, 1950
Creator:
Oliver, G. D. & Grisard, J. W.
Object Type:
Report
System:
The UNT Digital Library
Homogeneous Reactor Experiment Quarterly Progress Report [for] Period Ending August 31, 1950
Technical report containing the detailed design of the equipment within the reactor shield, reviewed in 1950. Contains various summaries on engineering design and development, reactor physics, chemical studies, and corrosion.
Date:
October 24, 1950
Creator:
Winters, C. E.; Gall, W. R.; Graham, C. B.; Quarles, L. R.; Stein, J. M.; Clewett, G. H. et al.
Object Type:
Report
System:
The UNT Digital Library
Wind-Tunnel Investigation of the Effects of a Jet Engine Nacelle on the Aerodynamic Characteristics of a 37.25 Degree Swept Back Wing at High Subsonic Speeds
Report presenting a wind-tunnel investigation to determine the aerodynamic characteristics of a wing-nacelle combination at high subsonic speeds. Lift, drag, pitching-moment, and ram-recovery data re presented for a range of Mach and Reynolds numbers.
Date:
October 24, 1950
Creator:
Boltz, Frederick W. & Buell, Donald A.
Object Type:
Report
System:
The UNT Digital Library
Construction Test : high Density Concrete Shielding
From introduction: "The test was performed to gain knowledge which would be useful for evaluating and improving currently planned methods for the design and construction of high density concrete shielding."
Date:
November 24, 1950
Creator:
Rice, L. L.
Object Type:
Report
System:
The UNT Digital Library
The Longitudinal Stability, Control Effectiveness, and Control Hinge Moment Characteristics Obtained From a Flight Investigation of a Canard Missile Configuration at Transonic and Supersonic Speeds
A 60 degree delta wing canard missile configuration was flight-tested at the Langley pilotless aircraft research station at Wallops Island, Va. The results include the longitudinal stability derivatives, control effectiveness, drag characteristics, and control-surface hinge-moment characteristics for a Mach number range of 0.7 to 1.45.
Date:
November 24, 1950
Creator:
Niewald, Roy J. & Moul, Martin T.
Object Type:
Report
System:
The UNT Digital Library
Analysis of the effects of wing interference on the tail contributions to the rolling derivatives
From Introduction: "This report presents calculations of the angularity of the air stream with respect to the vertical tail for a rolling airplane, the interference effects of the wing being taken into account. A discussion of the factors which enter into the calculations is given and equations for applying the side-wash results to the determination of the tail contributions to the rolling-stability derivatives are included. The results are compared with some available experimental data."
Date:
January 24, 1951
Creator:
Michael, William H., Jr.
Object Type:
Report
System:
The UNT Digital Library
The effects of camber and twist on the aerodynamic loading and stalling characteristics of a large-scale 45 degree swept-back wing
Report presenting pressure-distribution measurements on two large-scale semispan wing-fuselage models with 45 degrees of sweepback, an aspect ratio of 6, a taper ratio of 0.5, and 10-percent-thick sections normal to the quarter-chord line. Adding camber and twist to a wing significantly improved the upper surface loading of the wing at a lift coefficient of 0.4 through a reduction in the peak negative pressure coefficient. Results regarding loading characteristics and stalling characteristics are provided.
Date:
January 24, 1951
Creator:
Hunton, Lynn W. & Dew, Joseph K.
Object Type:
Report
System:
The UNT Digital Library
Effects of Spoiler on Airfoil Pressure Distribution and Effects of Size and Location of Spoilers on the Aerodynamic Characteristics of a Tapered Unswept Wing of Aspect Ratio 2.5 at a Mach Number of 1.90
Report presenting an investigation in the supersonic blowdown tunnel of spoilers on two unswept wing arrangements at Mach numbers of 1.90 and 1.96. The effect of pressure-distribution tests on an unswept airfoil in the presence of a fuselage but without tip effects indicated that spoilers could be oppositely deflected in a manner similar to flap-type ailerons to obtain roll effectiveness without loss in lift. Results regarding force and moment tests are also provided.
Date:
January 24, 1951
Creator:
Conner, D. William & Mitchell, Meade H., Jr.
Object Type:
Report
System:
The UNT Digital Library
A transonic-wing investigation in the Langley 8-foot high-speed tunnel at high subsonic Mach numbers and at a Mach number of 1.2 : wing-fuselage configuration having a wing of 60 degree sweepback, aspect-ratio 4, taper ratio 0.6, and NACA 65A006 airf
Report presenting a study of the effect of sweep on wings with the NACA 65A006 airfoil section in the 8-foot high-speed tunnel. This particular investigation included a wing with that airfoil section, 60 degrees of sweepback at the quarter chord, an aspect ratio of 4, and a taper ratio of 0.6. Results regarding force and moment characteristics and wake and downwash characteristics are provided.
Date:
January 24, 1951
Creator:
Wood, Raymond B. & Fleming, Frank F.
Object Type:
Report
System:
The UNT Digital Library
Zirconium Metal Fines Recovery: Interim Technical Report for May 15, 1950 to December 15, 1950
This report covers the laboratory and pilot plant investigation of the reclamation of the low hafnium zirconium fines resulting from the manufacture of zirconium sponge and zirconium crystal bar. The process investigated involved recovery of the zirconium as zirconium tetrachloride, by drying the fines in an atmosphere of nitrogen and subsequent chlorination of the fines with anhydrous hydrogen chloride at temperatures above the sublimation point of the product.
Date:
January 24, 1951
Creator:
Ogburn, S. C., Jr. & Reader, L. J.
Object Type:
Report
System:
The UNT Digital Library
Flight measurements of the wing-dropping tendency of a straight-wing jet airplane at high subsonic Mach numbers
From Summary: "Flight tests were conducted on a straight-wing fighter-type jet airplane to investigate the lateral-control characteristics associated with a wing-dropping tendency encountered at high subsonic Mach numbers. The chief factors found to account directly for the wing-dropping tendency were a progressive reduction in aileron-control effectiveness with increasing Mach number, and an increase in effective dihedral above a Mach number of 0.8 which made the lateral trim particularly sensitive to small changes in sideslip angle."
Date:
April 24, 1951
Creator:
Anderson, Seth B.; Ernst, Edward A. & Van Dyke, Rudolph D., Jr.
Object Type:
Report
System:
The UNT Digital Library
Investigation at low speed of the effectiveness and hinge moments of a constant-chord elevator on a large-scale triangular wing with section modification
Report presenting an investigation in the full-scale tunnel to determine the low-speed longitudinal, lateral, and hinge-moment control characteristics of a basic 60 degree delta wing of aspect ratio 2.31 with 10-percent-thick biconvex symmetrical airfoil sections. The wing was tested with a nose glove using NACA 65-010 section ordinates and a constant-chord plain semispan ailavator with two segments.
Date:
April 24, 1951
Creator:
Hawes, John G. & May, Ralph W., Jr.
Object Type:
Report
System:
The UNT Digital Library
Preliminary Results on the Determination of Thermal Neutron Flux in Water
This preliminary report follows the investigation on the determination of thermal neutron flux in water by the foil method.
Date:
April 24, 1951
Creator:
Klema, Ernest D. & Ritchie, R. H.
Object Type:
Report
System:
The UNT Digital Library