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Serial/Series Title
NACA Wartime Reports
117
NACA Research Memorandums
105
NACA Technical Notes
85
Atomic Energy Commission Reports
51
NACA Advanced Restricted Reports
45
NACA Memorandum Reports
40
NACA Technical Memorandums
27
NACA Technical Reports
27
United States Bureau of Mines Reports
22
NACA Advanced Confidential Reports
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466 Matching Results
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Experimental Investigation of the Effects of Sweepback on the Flutter of a Uniform Cantilever Wing With a Variably Located Concentrated Mass
Report presenting data from 95 subsonic flutter tests conducted in the flutter research tunnel on untapered cantilever wings with sweepback angles of 0, 45, and 60 degrees and carrying a single concentrated weight. The primary purpose of the investigation was to present experimental information to be used to evaluate analytical procedures for determining the flutter speed of weighted sweptback wings. The dynamic pressure, flutter velocity, Mach number, natural and flutter frequencies, and phase-angle relationships of the stresses for the natural and flutter frequencies are presented.
Date:
August 31, 1949
Creator:
Nelson, Herbert C. & Tomassoni, John E.
Object Type:
Report
System:
The UNT Digital Library
Flight Investigation at High-Subsonic, Transonic, and Supersonic Speeds to Determine Zero-Lift Drag of Bodies of Revolution Having Fineness Ratio of 6.04 and Varying Positions of Maximum Diameter
Report presenting a flight investigation of rocket-powered models at high-subsonic, transonic, and supersonic speeds to determine the zero-lift drag of fin-stabilized bodies of revolution differing in maximum diameter. All bodies had 6.04 fineness ratio and cut-off sterns with equal base area. The most favorable location out of the 20-percent, 40-percent, and 60-percent positions were evaluated for different speeds.
Date:
August 31, 1949
Creator:
Katz, Ellis R.
Object Type:
Report
System:
The UNT Digital Library
Investigation of Fretting by Microscopic Observation
"An experimental investigation, using microscopic observation and color motion photomicrographs of the action, was conducted to determine the cause of fretting. Glass and other noncorrosive materials, as well as metals, were used as specimens. A very simple apparatus vibrated convex surfaces in contact with stationary flat surfaces at frequencies of 120 cycles or less than l cycle per second, an amplitude of 0.0001 inch, and load of 0.2 pound" (p. 135).
Date:
August 31, 1949
Creator:
Godfrey, Douglas
Object Type:
Report
System:
The UNT Digital Library
A radar method of calibrating airspeed installations on airplanes in maneuvers at high altitudes and at transonic and supersonic speeds
A method of calibrating the static-pressure source of a pitot static airspeed installation on an airplane in level flight, dives, and other maneuvers at high altitude and at transonic and supersonic speeds is described. The method principally involves the use of radar-phototheodolite tracking equipment. The various sources of error in the method are discussed and sample calibrations are included.
Date:
August 31, 1949
Creator:
Zalovcik, John A.
Object Type:
Report
System:
The UNT Digital Library
Performance of Single-Stage Turbine of Mark 25 Torpedo Power Plant with Two Special Nozzles 2 - Efficiency with 20 Degrees-Inlet-Angle Rotor Blades
"A single-stage modification of the turbine from a Mark 25 torpedo power plant was investigated to determine the performance with two nozzle designs in combination with special rotor blades having a 20 inlet angle. The performance is presented in terms of blade, rotor, and brake efficiency as a function of blade-jet speed ratio for pressure ratios of 8, 15 (design), and 20. The blade efficiency with the nozzle having circular pas- sages (K) was equal to or higher than that with the nozzle having rectangular passages (J) for all pressure ratios and speeds investigated" (p. 1).
Date:
August 25, 1949
Creator:
Schum, Harold J. & Whitney, Warren J.
Object Type:
Report
System:
The UNT Digital Library
An apparatus for varying effective dihedral in flight with application to a study of tolerable dihedral on a conventional fighter airplane
From Summary: "An apparatus for varying effective dihedral in flight by means of servo actuation of the ailerons in response to sideslip angle is described. The results of brief flight tests of the apparatus on a conventional fighter airplane are presented and discussed. The results of an investigation employing the apparatus to determine the tolerable (safe for normal fighter operation) range of effective dihedral on the test airplane are presented."
Date:
August 24, 1949
Creator:
Kauffman, William M.; Liddell, Charles J., Jr.; Smith, Allan & Van Dyke, Rudolph D., Jr.
Object Type:
Report
System:
The UNT Digital Library
Effect of an Increase in Hull Length-Beam Ratio From 15 to 20 on the Hydrodynamic Characteristics of Flying Boats
Report presenting an investigation of the effect of hull length-beam ratio on the hydrodynamic characteristics of flying boats that extend to a length-beam ratio of 20. The results are compared with flying boats having a length-beam ratio of 15. Results regarding longitudinal stability, spray characteristics, take-off performance, taxiing and take-off behavior in waves, landing behavior in waves, and a summary chart are provided.
Date:
August 24, 1949
Creator:
Carter, Arthur W. & Whitaker, Walter E., Jr.
Object Type:
Report
System:
The UNT Digital Library
Performance of Single-Stage Turbine of Mark 25 Torpedo Power Plant with Two Special Nozzles 1 - Efficiency with 0.45-inch Rotor Blades
"An investigation was made of the first-stage turbine of a Mark 25 torpedo power plant to determine the performance of the unity with two nozzle configurations and a special rotor having 0.45-inch blades instead of the standard length of 0.40 inch. Both nozzles had smaller passages than the nozzles of similar shape that were previously investigated. The performance of the nozzle-blade combinations is evaluated in terms of brake, rotor, and blade efficiency as functions of blade-jet speed ratio for three pressure ratios" (p. 1).
Date:
August 23, 1949
Creator:
Schum, Harold J. & Whitney, Warren J.
Object Type:
Report
System:
The UNT Digital Library
The Beta-Gamma Surface Dosage Rate from Natural Uranium
From summary: "Report discussing the beta-gamma dosage rate at the surface of a natural uranium disc. Measurements were taken using a Ryerson electrometer and an extrapolation ionization chamber."
Date:
August 22, 1949
Creator:
Kalmon, Ben
Object Type:
Report
System:
The UNT Digital Library
Design of a Bubble-Cap Column to Replace Nitric Acid Concentrator
The following document presents designs and blueprints to the bubble-cap column built to replace a nitric acid concentrator.
Date:
August 22, 1949
Creator:
Wallingford, H.
Object Type:
Report
System:
The UNT Digital Library
A Rapid Colorimeric Method for the Determination of Phosphate in Uranium Waste Solutions
Report discussing tests of a new colorimetric method. From abstract: "A colorimetric method, which is a modification of the classical phosphomolybdic acid method, has been developed for the determination of phosphate in synthetic uranium waste solutions...The chief advantage of the method, over those presently included in HW Manuals, is the rapidity with which determinations may be carried out."
Date:
August 22, 1949
Creator:
Sege, C. A. & Ice, C. H.
Object Type:
Report
System:
The UNT Digital Library
The Solvent-Extraction Performance of Redox IC Columns (ANL June 1948 Flowsheet) Using Raschig Ring Packing, and Unirradiated Uranium: Redox Technical Study No. 14
A report which summarizes the performance data obtained from Redox solvent extraction IC Column studies made prior to January 15, 1949 in accordance with conditions of the A.N.L. June 1, 1948, Flowsheet.
Date:
August 22, 1949
Creator:
Hartzell, L. O.; Woodfield, F. W. & Bradley, J. G.
Object Type:
Report
System:
The UNT Digital Library
Wind-Tunnel Tests of a 0.16-Scale Model of the Douglas MX-656 Airplane at High Subsonic Speeds. 2 - Wing and Fuselage Pressure Distribution
From Summary: "Measurements of wing and fuselage pressure distributions were made at low and high subsonic Much numbers on a 0.16-scale model of the projected MX-656 research airplane. The MX-656 is a supersonic design utilizing a low-aspect-ratio wing and tail. Pressure-distribution measurements indicated that, although the critical Mach number of the wing was approximately 0.81 at 0 degree angle of attack, compressibility effects were of little significance below a Mach number of at least 0.90. The principal effect of compressibility was an increase in the pressure gradient over the after 30 percent of the wing chord, causing a tendency for the flow to separate."
Date:
August 22, 1949
Creator:
Cleary, Joseph W. & Mellenthin, Jack A.
Object Type:
Report
System:
The UNT Digital Library
The Influence of Infection on the Hematological Effects and Mortality Following Mid-Lethal X-Radiation
Report describing the blood cultures of fifty-four dogs that were exposed mid-lethal whole body x-radiation.
Date:
August 18, 1949
Creator:
University of Rochester. Atomic Energy Project.
Object Type:
Report
System:
The UNT Digital Library
Initial Experiments on the Brookhaven Reactor. VI. Fast Source Correction for Diffusion Length Measurements on BNL Reactor
In a manner somewhat analogue to that employed by R. Margulies in his memo (BNL Log No. C-2985) on fast source corrections in sigma piles, corrections to be applied to the data obtained on the laid-up graphite in the BNL reactor have been calculated. The correction was computed for a Ra-Be source using the data of Seren and using a standard graphite density for the BNL pile of 1.69. Values of the correction for different experimental sets of data were computed for each of three different diffusion lengths measured parallel to the channels. A correction for diffusion lengths perpendicular to the channels was also determined.
Date:
August 18, 1949
Creator:
Weil, J. W.
Object Type:
Report
System:
The UNT Digital Library
Preliminary Measurements of the Dynamic Lateral Stability Characteristics of the Douglas D-588-II (BuAero No. 37974) Airplane
"This paper presents some data on the dynamic lateral stability characteristics of the Douglas D-558-II (BuAero No. 37974) airplane. For the airplane in the clean condition, the lateral oscillations are lightly damped. In the landing condition, the airplane performs a constant-amplitude lateral oscillation" (p. 1).
Date:
August 18, 1949
Creator:
Sjoberg, Sigurd A.
Object Type:
Report
System:
The UNT Digital Library
Special Irradiation of Temperature-Indicating Liquid: Final Report--Production Test 105-266-P
A report discussing an experiment conducted to determine the effect of radiation on the melting point of Tempilaq, a commercially available, temperature-indicating liquid.
Date:
August 18, 1949
Creator:
Carbon, M. W.
Object Type:
Report
System:
The UNT Digital Library
Spectra and diffusion in a round turbulent jet
"In a round turbulent jet at room temperature, measurement of the shear correlation coefficient as a function of frequency (through band-pass filters) has given a rather direct verification of Kolmogoroff's local-isotropy hypothesis. One-dimensional power spectra of velocity and temperature fluctuations, measured in unheated and heated jets, respectively, have been contrasted. Under the same conditions, the two corresponding transverse correlation functions have been measured and compared" (p. 1).
Date:
August 17, 1949
Creator:
Corrsin, Stanley & Uberoi, Mahinder S.
Object Type:
Report
System:
The UNT Digital Library
The Coulometric Determination of Acetic Acid
Abstract: "Small amounts of acetic acid, equivalent to 400 ul. of 0.3 to 0.13 g/L. can be titrated coulonatrically in the presence of a 10 to 25-fold excess of HN03 in 70%, isopropanol. An accuracy of +/- 0.1% and a precision of +/- 8.5% (99% limite) are obtained.
Date:
August 16, 1949
Creator:
Carson, W. N. & Ko, Roy
Object Type:
Report
System:
The UNT Digital Library
An NACA Vane-Type Angle-of-Attack Indicator for use at Subsonic and Supersonic Speeds
A vane-type angle-of-attack indicator suitable for measurements at both subsonic and supersonic speeds has been developed by the National Advisory Committee for Aeronautics. A brief history is given of the development, and a wind-tunnel calibration of the indicator is presented, together with a discussion of the corrections to be applied to the indicated readings.
Date:
August 16, 1949
Creator:
Mitchell, Jesse L. & Peck, Robert F.
Object Type:
Report
System:
The UNT Digital Library
On Reflection of Shock Waves from Boundary Layers
Measurements are presented at Mach numbers from about 1.3 to 1.5 of reflection characteristics and the relative upstream influence of shock waves impinging on a flat surface with both laminar and turbulent boundary layers. The difference between impulse and step waves is discussed and their interaction with the boundary layer is compared. General considerations on the experimental production of shock waves from wedges and cones and examples of reflection of shock waves from supersonic shear layers are also presented.
Date:
August 16, 1949
Creator:
Liepmann, H. W.; Roshko, A. & Dhawan, S.
Object Type:
Report
System:
The UNT Digital Library
Preliminary Aerodynamic Investigation of the Effect of Camber on a 60 Degree Delta Wing with Round and Beveled Leading Edges
Memorandum presenting an exploratory investigation to determine the aerodynamic effects of camber on a 60 degree apex delta-wing model conducted in the 300 mph 7- by 10-foot tunnel. Camber variation was accomplished through the deflection of full-span round and 25 degree beveled leading-edge flaps on a flat-sided triangular plan-form wing.
Date:
August 16, 1949
Creator:
Riebe, John M. & Fikes, Joseph E.
Object Type:
Report
System:
The UNT Digital Library
Procedures in Magnetic Measurements at the University of California Radiation Laboratory, Berkeley: Fields Which are Constant or Vary Slowly with Time
The flux standard is a device which will give a known flux-linkage change to be used as a calibration. At the Radiation Laboratory, two types of flux standards are used, a stationary type and a portable type.
Date:
August 16, 1949
Creator:
Richardson, Robert E.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic Study of a Wing-Fuselage Combination Employing a Wing Swept Back 63 Degrees: Characteristics Throughout the Subsonic Speed Range With the Wing Cambered and Twisted for a Uniform Load at a Lift Coefficient of 0.25
Report presenting wind-tunnel testing to determine the independent effects of Mach and Reynolds numbers on the aerodynamic characteristics of a wing-fuselage combination with a wing with the leading edge swept back 63 degrees and with camber and twist. Results regarding the fuselage alone and the effects of camber and twist are also provided.
Date:
August 15, 1949
Creator:
Jones, J. Lloyd & Demele, Fred A.
Object Type:
Report
System:
The UNT Digital Library