Resource Type
Serial/Series Title
NACA Research Memorandums
173
Atomic Energy Commission Reports
61
NACA Technical Reports
30
Hanford Works Reports
20
HW (Series)
16
Oak Ridge National Laboratory Reports
15
University of California Radiation Laboratory Reports
12
AEC research and development report
6
AECU (Series)
6
BNL (Series)
6
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A Reconnaissance For Oil Near Quanah, Hardeman County Texas
This report documents the examination for oil in the vicinity of Quanah, Hardeman County Texas during the fall of 1914.
Date:
October 9, 1915
Creator:
Wegemann, Carroll H.
Object Type:
Report
System:
The UNT Digital Library
Preliminary Report on the Problem of the Atmosphere in Relation to Aeronautics
A report to the Weather Bureau, Washington DC, from the chairman of the Subcommittee on the Atmosphere in Relation to Aeronautics describing the activities accomplished and the proposal of work to be undertaken by the subcommittee.
Date:
November 9, 1915
Creator:
Marvin, Charles F.
Object Type:
Report
System:
The UNT Digital Library
Review of the Grizzly and Big Brown Bears of North America (Genus Ursus): with Description of a New Genus, Vetularctos
Discusses distribution,sexual and age differences, specimens, and classification of North American grizzly and big brown bears. Describes and lists locations of species and subspecies. Mentions Vetularctos, a new genus related to Ursus.
Date:
February 9, 1918
Creator:
Merriam, C. Hart
Object Type:
Report
System:
The UNT Digital Library
Pressure Distribution Tests on PW-9 Wing Models From -18 Degree Through 90 Degree Angle of Attack
"At the request of the Army Air Corps, an investigation of the pressure distribution over PW-9 wing models was conducted in the atmospheric wind tunnel of the National Advisory Committee for Aeronautics. The primary purpose of these tests was to obtain wind-tunnel data on the load distribution on the cellule to be correlated with similar information obtained in flight tests, both to be used for design purposes. Because of the importance of the conditions beyond the stall as affecting the control and stability, this investigation was extended through 90 degree angle of attack" (p. 335).
Date:
April 9, 1928
Creator:
Loeser, Oscar E., Jr.
Object Type:
Report
System:
The UNT Digital Library
An Investigation of the Aerodynamic Characteristics of an Airplane Equipped with Several Different Sets of Wings
This investigation was conducted by the National Advisory Committee for Aeronautics at Langley Field, Va., at the request of the Army Air Corps, for the purpose of comparing the full scale lift and drag characteristics of an airplane equipped with several sets of wings of commonly used airfoil sections. A Sperry Messenger Airplane with wings of R.A.F.-15, U.S.A.-5, U.S.A.-27, and Gottingen 387 airfoil sections was flown and the lift and drag characteristics of the airplane with each set of wings were determined by means of glide tests. The results are presented in tabular and curve form.
Date:
July 9, 1928
Creator:
Crowley, J. W., Jr. & Green, M. W.
Object Type:
Report
System:
The UNT Digital Library
The pressure distribution over the horizontal and vertical tail surfaces of the F6C-4 pursuit airplane in violent maneuvers
"This investigation of the pressure distribution on the tail surfaces of a pursuit airplane in violent maneuvers was conducted for the purpose of determining the maximum loads likely to be encountered on these surfaces in flight. The information is a part of that needed for a revision of existing loading specifications to bring these into closer agreement with the actual flight conditions. A standard F6C-4 airplane was used and the pressure distribution over the right horizontal and complete vertical tail surfaces was recorded throughout violent maneuvers. The results show that the existing loading specifications do not conform satisfactorily to the loadings existent in critical conditions, and in some cases were exceeded by the loads obtained" (p. 539).
Date:
July 9, 1928
Creator:
Rhode, R. V.
Object Type:
Report
System:
The UNT Digital Library
The Gaseous Explosive Reaction at Constant Pressure: The Reaction Order and Reaction Rate
The data given in this report covers the explosive limits of hydrocarbon fuels. Incidental to the purpose of the investigation here reported, the explosive limits will be found to be expressed for the condition of constant pressure, in the fundamental terms of concentrations (partial pressures) of fuel and oxygen.
Date:
May 9, 1929
Creator:
Stevens, F. W.
Object Type:
Report
System:
The UNT Digital Library
Present Status of Aircraft Instruments
This report gives a brief description of the present state of development and of the performance characteristics of instruments included in the following group: speed instruments, altitude instruments, navigation instruments, power-plant instruments, oxygen instruments, instruments for aerial photography, fog-flying instruments, general problems, summary of instrument and research problems. The items considered under performance include sensitivity, scale errors, effects of temperature and pressure, effects of acceleration and vibration, time lag, damping, leaks, elastic defects, and friction.
Date:
October 9, 1930
Creator:
Subcommittee on Instruments
Object Type:
Report
System:
The UNT Digital Library
The vertical wind tunnel of the National Advisory Committee for Aeronautics
"The vertical open-throat wind tunnel of the National Advisory Committee for Aeronautics is described in this report. The tunnel was built mainly for studying the spinning characteristics of airplane models, but may be used as well for the usual types of wind-tunnel tests. A special spinning balance is being developed to measure the desired forces and moments with the model simulating the spin of an airplane. Satisfactory air flow has been attained with a velocity that is uniform over the jet to within plus or minus 0.5 per cent" (p. 499).
Date:
February 9, 1931
Creator:
Wenzinger, Carl J. & Harris, Thomas A.
Object Type:
Report
System:
The UNT Digital Library
The Theory of Wind-Tunnel Wall Interference
This report outlines the development of a general theory for the calculation of the effect of the boundaries of the air stream on the flow past an airfoil. Analytical treatments are given for tunnels with horizontal boundaries only, with vertical boundaries only, and with a bottom boundary only. Formulas are developed for the tunnel wall interference in each case for an airfoil located at the center of the tunnel. The correction is given as a function of the width to height ratio of the tunnel.
Date:
October 9, 1931
Creator:
Theodorsen, Theodore
Object Type:
Report
System:
The UNT Digital Library
The N.A.C.A. Tank: A High-Speed Towing Basin for Testing Models of Seaplane Floats
"This report describes the high-speed model towing basin of the National Advisory Committee for Aeronautics, usually referred to as the NACA Tank. The purpose of this piece of equipment is to enable the Committee to provide information and data regarding the performance of seaplanes on the water analogous to the information furnished concerning the performance of airplanes in the air" (p. 535).
Date:
June 9, 1933
Creator:
Truscott, Starr
Object Type:
Report
System:
The UNT Digital Library
The drag of airplane wheels, wheel fairings, and landing gears - 1
This report presents the results of tests made in the 7-by 10-foot wind tunnel and in the 20-foot tunnel of the National Advisory Committee for Aeronautics to determine the drag of a number of airplane wheels, wheel fairings, and landing gears designed or selected for an airplane of 3,000 pounds gross weight. All tests were made on full-size models; those in the 7-by 10-foot tunnel were made at air speeds up to 80 miles per hour and those in the 20-foot tunnel were made at air speeds up to 100 miles per hour. Although most of the landing-gear tests were made in conjunction with a fuselage and at 0 degree pitch angle, some of the tests were made in conjunction with fuselage plus wings and a radial air-cooled engine and at pitch angles from -5 degrees to 6 degrees to obtain an indication of the general effect of these various items on landing-gear drag.
Date:
February 9, 1934
Creator:
Herrnstein, William H., Jr. & Biermann, David
Object Type:
Report
System:
The UNT Digital Library
The influence of tip shape on the wing load distribution as determined by flight tests
"Pressure measurements were made in flight on the right upper wing of an M-3 airplane. The effects of tip plan form, washout, and transverse camber were investigated with eight tip forms in unyawed conditions through the range of positive lift coefficients from zero lift to the stall. The conclusion is that the tip plan form does not influence the span distribution of the coefficients of normal force and moment. It is shown inferentially that temperature, humidity, and the aging of the wood and fabric wing structure used on the M-3 airplane have an appreciable influence on the load distribution" (p. 479).
Date:
June 9, 1934
Creator:
Rhode, Richard V.
Object Type:
Report
System:
The UNT Digital Library
Distribution and Regularity of Injection From a Multicylinder Fuel-Injection Pump
This report presents the results of performance test conducted on a six-cylinder commercial fuel-injection pump that was adjusted to give uniform fuel distribution among the cylinders at a throttle setting of 0.00038 pound per injection and a pump speed of 750 revolutions per minute. The throttle setting and pump speed were then varied through the operating range to determine the uniformity of distribution and regularity of injection.
Date:
April 9, 1935
Creator:
Rothrock, A. M. & Marsh, E. T.
Object Type:
Report
System:
The UNT Digital Library
Combustion in a Bomb With a Fuel-Injection System
"Fuel injected into a spherical bomb filled with air at a desired density and temperature could be ignited with a spark a few thousandths of a second after injection, an interval comparable with the ignition lag in fuel-injection engines. The effect of several variables on the extent and rate of combustion was investigated: time intervals between injection and ignition of fuel of 0.003 to 0.06 second and one of 5 minutes; initial air temperatures of 100 degrees C. to 250 degrees C.; initial air densities equivalent to 5, 10, and 15 absolute atmospheres pressure at 100 degrees C.; and air-fuel ratios of 5 to 25" (p. 107).
Date:
August 9, 1935
Creator:
Cohn, Mildred & Spencer, Robert C.
Object Type:
Report
System:
The UNT Digital Library
Column Strength of Tubes Elastically Restrained Against Rotation at the Ends
Report presents the results of a study made of the effects of known end restraint on commercially available round and streamline tubing of chromium-molybdenum steel, duralumin, stainless steel, and heat-treated chromium-molybdenum steel; and a more accurate method than any previously available, but still a practical method, was developed for designing compression members in riveted or welded structures, particularly aircraft. Two hundred specimens were tested as short, medium-length, and long columns with freely supported ends or elastically restrained ends. Tensile and compressive tests were made on each piece of original tubing from which column specimens were cut.
Date:
September 9, 1937
Creator:
Osgood, William R.
Object Type:
Report
System:
The UNT Digital Library
Investigation in the 7-by-10 Foot Wind Tunnel of Ducts for Cooling Radiators within an Airplane Wing
Report presents the results of an investigation made in the NACA 7 by 10-foot wind tunnel of a large-chord wing model with a duct to house a simulated radiator suitable for a liquid-cooled engine. The duct was expanded to reduce the radiator losses, and the installation of the duct and radiator was made entirely within the wing to reduce form and interference drag. The tests were made using a two-dimensional-flow setup with a full-span duct and radiator. Section aerodynamic characteristics of the basic airfoil are given and also curves showing the characteristics of the various duct-radiator combinations.
Date:
June 9, 1938
Creator:
Harris, Thomas A. & Recant, Isidore G.
Object Type:
Report
System:
The UNT Digital Library
Pressure available for cooling with cowling flaps
Report presents the results of a full-scale investigation conducted in the NACA 20-foot tunnel to determine the pressure difference available for cooling with cowling flaps. The flaps were applied to an exit slot of smooth contour at 0 degree flap angle. Flap angles of 0 degree, 15 degrees, and 30 degrees were tested. Two propellers were used; propeller c which has conventional round blade shanks and propeller f which has airfoil sections extending closer to the hub. The pressure available for cooling is shown to be a direct function of the thrust disk-loading coefficient of the propeller.
Date:
May 9, 1940
Creator:
Stickle, George W.; Naiman, Irven & Crigler, John L.
Object Type:
Report
System:
The UNT Digital Library
A study by high-speed photography of combustion and knock in a spark-ignition engine
"The study of combustion in a spark-ignition engine given in Technical Report no. 704 has been continued. The investigation was made with the NACA high-speed motion-picture camera and the NACA optical engine indicator. The camera operates at the rate of 40,000 photographs a second and makes possible the study of phenomena occurring in time intervals as short as 0.000025 second. Photographs are presented of combustion without knock and with both light and heavy knocks, the end zone of combustion being within the field of view" (p. 15).
Date:
December 9, 1941
Creator:
Miller, Cearcy D.
Object Type:
Report
System:
The UNT Digital Library
Methods used in the NACA tank for the investigation of the longitudinal-stability characteristics of models of flying boats
Report presents the results of tests of longitudinal stability characteristics of models of several flying boats conducted in the NACA Tank No. 1. These investigations were made for the purpose of (1) determining suitable methods for evaluating the stability characteristics of models of flying boats, and (2) determining the design parameters which have an important effect on the porpoising. This report is mainly concerned with the construction of suitable models, the apparatus, and methods used in the tests. The effect of changes in some design parameters is discussed.
Date:
September 9, 1942
Creator:
Olson, Roland E. & Land, Norman S.
Object Type:
Report
System:
The UNT Digital Library
Temperature Effect in Homogeneous Pile
Some idealized considerations of the temperature field in the homogeneous pile are given. It is crudely estimated that the effective mean temperature rise of the pile to be used in calculating the k loss is something like 3/4 the rise in temperature of the slurry in passing through the pile.
Date:
December 9, 1943
Creator:
Young, Gale Jay
Object Type:
Report
System:
The UNT Digital Library
An Analytical Method for Determining Hydrogen in Tuballoy
Technical report describing a gasometrical method for the determination of H2 in extruded U rods.
Date:
February 9, 1944
Creator:
Russell, H. W. & Nelson, H. R.
Object Type:
Report
System:
The UNT Digital Library
Ames Project, Chemical Research - General, for the Period September 10, 1944 to October 10, 1944
Technical report with short articles on (1) Uranium-oxygen system compositions UO2 to U3O3; (2) Thorium hydride; (3) Production of cerium; and (4) Production of thorium.
Date:
November 9, 1944
Creator:
pedding, F. H. (Frank Harold), 1902- & Wilhelm, H. A.
Object Type:
Report
System:
The UNT Digital Library
Charts for the Determination of Wing Torsional Stiffness Required for Specified Rolling Characteristics or Aileron Reversal Speed
From Summary :"A series of charts are presented by which the wing torsional stiffness required to meet a given standard of rolling effectiveness may be quickly determined. The charts may also be used to obtain quickly the aileron reversal speed and the variation of the loss in rolling effectiveness with airspeed. The charts apply to linearly tapered wings and elliptical wings of tubular-shell construction having various aspect ratios with aileron span and location of ailerons as variables. In the derivation of the charts, induced lift effects have been taken into account and the form of the wing-torsional-stiffness curve has been assumed."
Date:
November 9, 1944
Creator:
Pearson, Henry A. & Aiken, William S., Jr.
Object Type:
Report
System:
The UNT Digital Library