Resource Type
Serial/Series Title
NACA Research Memorandums
183
Atomic Energy Commission Reports
63
Oak Ridge National Laboratory Reports
33
Hanford Works Reports
26
NACA Technical Reports
24
University of California Radiation Laboratory Reports
21
HW (Series)
16
ORNL (Series)
12
CF (Series)
11
AEC research and development report
10
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Results of a Biological Survey of the San Francisco Mountain Region and Desert of the Little Colorado, Arizona
Brief summary of a biological survey of the Painted Desert, specifically the San Francisco Mountain region, and the Grand Canyon (Cañon).
Date:
September 11, 1890
Creator:
Merriam, C. Hart & Stejneger, Leonhard
Object Type:
Report
System:
The UNT Digital Library
A Reconnaissance in Palo Pinto County, Texas : With Special Reference to Oil and Gas
This document reports the presence of oil and gas in Palo Pinto County, Texas, as studied by the United States Geological Survey in the fall of 1914.
Date:
September 11, 1915
Creator:
Wegemann, Carroll H.
Object Type:
Report
System:
The UNT Digital Library
Tests of Large Columns with H-Shaped Sections
Report issued by the Bureau of Standards over studies conducted on h-shaped columns. Physical and chemical tests were conducted on different types of columns. The results are presented and discussed. This report includes tables, illustrations, and photographs.
Date:
June 11, 1926
Creator:
Tuckerman, L. B. & Stang, A. H.
Object Type:
Report
System:
The UNT Digital Library
The comparative performance of an aviation engine at normal and high inlet air temperatures
"This report presents some results obtained during an investigation to determine the effect of high inlet air temperature on the performance of a Liberty 12 aviation engine. The purpose of this investigation was to ascertain, for normal service carburetor adjustments and a fixed ignition advance, the relation between power and temperature for the range of carburetor air temperatures that may be encountered when supercharging to sea level pressure at altitudes of over 20,000 feet and without intercooling when using plain aviation gasoline and mixtures of benzol and gasoline" (p. 409).
Date:
February 11, 1927
Creator:
Gardiner, Arthur W. & Schey, Oscar W.
Object Type:
Report
System:
The UNT Digital Library
Effect of variation of chord and span of ailerons on hinge moments at several angles of pitch
This report presents the results of an investigation of the hinge moments of ailerons of various chords and spans on two airfoils having the Clark Y and USA-27 wing sections, supplementing the investigations described in NACA-TR-298 and NACA-TR-343, of the rolling and yawing moments due to similar ailerons on these two airfoil sections. The measurements were made at various angles of pitch, but at zero angle of roll and yaw, the wing chord being set at an angle of +4 degrees to the fuselage axis.
Date:
August 11, 1930
Creator:
Monish, B. H.
Object Type:
Report
System:
The UNT Digital Library
Coefficients of discharge of fuel-injection nozzles for compression-ignition engines
"This report presents the results of an investigation to determine the coefficients of discharge of nozzles with small, round orifices of the size used with high-speed compression-ignition engines. The injection pressures and chamber back pressures employed were comparable to those existing in compression-ignition engines during injection. The construction of the nozzles was varied to determine the effect of the nozzle design on the coefficient. Tests were also made with nozzles assembled in an automatic injection valve, both with a plain and with a helically grooved stem" (p. 193).
Date:
September 11, 1930
Creator:
Gelalles, A. G.
Object Type:
Report
System:
The UNT Digital Library
Airfoil section characteristics as affected by protuberances
From Introduction: "The present report deals with another phase of the investigation; that is, the effects on airfoil section characteristics of protuberances extending along the entire span from the airfoil surface."
Date:
July 11, 1932
Creator:
Jacobs, Eastman N.
Object Type:
Report
System:
The UNT Digital Library
Working Charts for the Determination of the Lift Distribution Between Biplane Wings
"In this report are presented empirical working charts from which the distribution of lift between wings, that is the fraction of the total lift borne by each, can be determined in the positive lift range for any ordinary biplane cellule whose individual wings have the same profile. The variables taken directly into account include airfoil section, stagger, gap/chord ratio, decalage, chord ratio, and overhang. It is shown that the influence of unequal sweepback and unequal dihedral in upper and lower wings may be properly provided for by utilizing the concepts of average stagger and average gap/chord ratio, respectively" (p. 93).
Date:
July 11, 1932
Creator:
Kuhn, Paul
Object Type:
Report
System:
The UNT Digital Library
Some Factors Affecting Combustion in an Internal-Combustion Engine
"An investigation of the combustion of gasoline, safety, and diesel fuels was made in the NACA combustion apparatus under conditions of temperature that permitted ignition by spark with direct fuel injection, in spite of the compression ratio of 12.7 employed. The influence of such variables as injection advance angle, jacket temperature, engine speed, and spark position was studied. The most pronounced effect was that an increase in the injection advance angle (beyond a certain minimum value) caused a decrease in the extent and rate of combustion. In almost all cases combustion improved with increased temperature" (p. 125).
Date:
September 11, 1934
Creator:
Rothrock, A. M. & Cohn, Mildred
Object Type:
Report
System:
The UNT Digital Library
Wind-Tunnel and Flight Tests of Slot-Lip Ailerons
"The slot-lip ailerons developed by the NACA consist of a flap-type spoiler with an adjoining continuously open slot. The ailerons were developed in an investigation of the delayed response, or lag, of spoiler-type lateral controls. This report presents the results of tests of these slot-lip ailerons made on wing models in the 7 by 10-foot wind tunnel, on a Fairchild 22 airplane in the full-scale wind tunnel and in flight, and on the Weick W1-A airplane in flight" (p. 537).
Date:
June 11, 1937
Creator:
Shortal, Joseph A.
Object Type:
Report
System:
The UNT Digital Library
Stability of Castering Wheels for Aircraft Landing Gears
"A theoretical study was made of the shimmy of castering wheels. The theory is based on the discovery of a phenomenon called kinematic shimmy. Experimental checks, use being made of a model having low-pressure tires, are reported and the applicability of the results to full scale is discussed. Theoretical methods of estimating the spindle viscous damping and the spindle solid friction necessary to avoid shimmy are given. A new method of avoiding shimmy -- lateral freedom -- is introduced" (p. 147).
Date:
August 11, 1937
Creator:
Kantrowitz, Arthur
Object Type:
Report
System:
The UNT Digital Library
Two-Dimensional Subsonic Compressible Flow Past Elliptic Cylinders
"The method of Poggi is used to calculate, for perfect fluids, the effect of compressibility upon the flow on the surface of an elliptic cylinder at zero angle of attack and with no circulation. The result is expressed in a closed form and represents a rigorous determination of the velocity of the fluid at the surface of the obstacle insofar as the second approximation is concerned. Comparison is made with Hooker's treatment of the same problem according to the method of Janzen and Rayleight and it is found that, for thick elliptic cylinders, the two methods agree very well" (p. 245).
Date:
February 11, 1938
Creator:
Kaplan, Carl
Object Type:
Report
System:
The UNT Digital Library
Methods of Testing Hosiery
Report issued by the Bureau of Standards discussing laboratory testing of hosiery to determine production costs and to make comparisons. Different manufacturing methods and possible defects are presented. This report includes tables, illustrations, and photographs.
Date:
October 11, 1938
Creator:
Schenke, E. Max & Shearer, Howard E.
Object Type:
Report
System:
The UNT Digital Library
Free-spinning wind-tunnel tests of a low-wing monoplane with systematic changes in wings and tails V: effect of airplane relative density
The reported tests are a continuation of an NACA investigation being made in the free-spinning wind tunnel to determine the effects of independent variations in load distribution, wing and tail arrangement, and control disposition on the spin characteristics of airplanes. The standard series of tests was repeated to determine the effect of airplane relative density. Tests were made at values of the relative-density parameter of 6.8, 8.4 (basic), and 12.0; and the results were analyzed. The tested variations in the relative-density parameter may be considered either as variations in the wing loading of an airplane spun at a given altitude, with the radii of gyration kept constant, or as a variation of the altitude at which the spin takes place for a given airplane. The lower values of the relative-density parameter correspond to the lower wing loadings or to the lower altitudes of the spin.
Date:
January 11, 1940
Creator:
Seidman, Oscar & Neihouse, A. I.
Object Type:
Report
System:
The UNT Digital Library
Wind-tunnel investigation of air inlet and outlet openings on a streamline body
In connection with the general problem of providing air flow to an aircraft power plant located within a fuselage, an investigation was conducted in the Langley 8-foot high-speed tunnel to determine the effect on external drag and pressure distribution of air inlet openings located at the nose of a streamline body. Air outlet openings located at the tail and at the 21-percent and 63-percent stations of the body were also investigated. Boundary layer transition measurements were made and correlated with the force and the pressure data. Individual openings were investigated with the aid of a blower and then practicable combinations of inlet and outlet openings were tested. Various modifications to the internal duct shape near the inlet opening and the aerodynamic effects of a simulated gun in the duct were also studied. The results of the tests suggested that outlet openings should be designed so that the static pressure of the internal flow at the outlet would be the same as the static pressure of the external flow in the vicinity of the opening.
Date:
September 11, 1940
Creator:
Becker, John V.
Object Type:
Report
System:
The UNT Digital Library
Propeller charts for the determination of the rotational speed for the maximum ratio of the propulsive efficiency to the specific fuel consumption
A set of propeller operating efficiency charts, based on a coefficient from which the propeller rotational speed has been eliminated, is presented. These charts were prepared with data obtained from tests of full-size metal propellers in the NACA propeller-research tunnel. Working charts for nine propeller-body combinations are presented, including results from tests of dual-rotating propellers. These charts are to be used in the calculation of the range and the endurance of airplanes equipped with constant-speed propellers in which, for given flight conditions, it is desired to determine the propeller revolution speed that gives the maximum ratio of the propulsive efficiency to the specific fuel consumption. The coefficient on which the charts are based may be written in the form of a thrust coefficient or a thrust-power coefficient. A method of using the charts is outlined and sample computations for a typical airplane are included.
Date:
December 11, 1940
Creator:
Biermann, David & Conway, Robert N.
Object Type:
Report
System:
The UNT Digital Library
Exhaust-stack nozzle area and shape for individual cylinder exhaust-gas jet-propulsion system
This report presents the results of an investigation conducted on the effect of exhaust-stack nozzle area, shape, and length on engine power, jet thrust, and gain in net thrust (engine propeller plus jet). Single-cylinder engine data were obtained using three straight stacks 25, 44, and 108 inches in length; an S-shaped stack, a 90 degree bend, a 180 degree bend, and a short straight stack having a closed branch faired into it. Each stack was fitted with nozzles varying in exit area from 0.91 square inch to the unrestricted area of the stack of 4.20 square inches. The engine was generally operated over a range of engine speeds from 1300 to 2100 r.p.m, inlet-manifold pressures from 22 to 30 inches of mercury absolute, and a fuel-air ratio of 0.08. The loss in engine power, the jet thrust, and the gain in net thrust are correlated in terms of several simple parameters. An example is given for determining the optimum nozzle area and the overall net thrust.
Date:
August 11, 1942
Creator:
Pinkel, Benjamin; Turner, L. Richard; Voss, Fred & Humble, Leroy V.
Object Type:
Report
System:
The UNT Digital Library
Propellers in yaw
It was realized as early as 1909 that a propeller in yaw develops a side force like that of a fin. In 1917, R. G. Harris expressed this force in terms of the torque coefficient for the unyawed propeller. Of several attempts to express the side force directly in terms of the shape of the blades, however, none has been completely satisfactory. An analysis that incorporates induction effects not adequately covered in previous work and that gives good agreement with experiment over a wide range of operating conditions is presented. The present analysis shows that the fin analogy may be extended to the form of the side-force expression and that the effective fin area may be taken as the projected side area of the propeller.
Date:
October 11, 1943
Creator:
Ribner, Herbert S.
Object Type:
Report
System:
The UNT Digital Library
Report on Methods of Preparation of Inorganic Fluorides
From abstract: "Frequently it has been desirable to prepare pure anhydrous metal fluorides. Several general methods have proved satisfactory depending on the type of fluoride to be prepared."
Date:
November 11, 1943
Creator:
Priest, H. F.
Object Type:
Report
System:
The UNT Digital Library
The Fission Neutron Spectrum of 25
Abstract: "Photographic plates have been used to measure the energy of neutrons from the fission of 25. The spectrum as inferred from the ranges of 850 protons recoiling in the forward direction shows a very wide maximum at ~1.5 Mev with an exponentially decreasing high energy tail which extends beyond 7 Mev. The minimum energy neutrons recorded were ~700 kv. If the spectrum is extrapolated to zero, one finds that this average neutron energy is about 1.85 Mev. The stopping power of the plates was calibrated by the use of monochromatic neutrons from the Li-7(pn) Be-7 reaction and the d-d reaction."
Date:
February 11, 1944
Creator:
Richards, Hugh T. & Perlman, Isadore
Object Type:
Report
System:
The UNT Digital Library
Recalculation of the Critical Size and Multiplication Constant of a Homogeneous UO2 - D2O Mixtures
The multiplication constant and optimal concentration of a slurry pile is recalculated on the basis of Mitchell's recent experiments on resonance absorption. The smallest chain reacting unit contains 45 to 55 m3 of D2O.
Date:
February 11, 1944
Creator:
Wigner, Eugene Paul, 1902-1995; Weinberg, Alvin Martin, 1915-2006 & Stephenson, J.
Object Type:
Report
System:
The UNT Digital Library
Metallurgical Laboratory, Chemical Research - Analytical, Report for the Month Ending July 1, 1944
Technical report containing short reports on (1) Mass spectrometer studies; (2) Purification of heavy water; and (3) Equilibration studies.
Date:
August 11, 1944
Creator:
Hogness, T. R. (Thorfin Rusten), 1894-; Ashcraft, E. B.; McKinney, D. S. & Voskuyl, R. J.
Object Type:
Report
System:
The UNT Digital Library
Preknock vibrations in a spark-ignition engine cylinder as revealed by high-speed photography
"The high-speed photographic investigation of the mechanics of spark-ignition engine knock recorded in three previous reports has been extended with use of the NACA high-speed camera and combustion apparatus with a piezoelectric pressure pickup in the combustion chamber. The motion pictures of knocking combustion were taken at the rate of 40,000 frames per second. Existence of the preknock vibrations in the engine cylinder suggested in Technical Report no.727 has been definitely proved and the vibrations have been analyzed both in the high-speed motion pictures and the pressure traces" (p. 223).
Date:
September 11, 1944
Creator:
Miller, Cearcy D. & Logan, Walter O., Jr.
Object Type:
Report
System:
The UNT Digital Library
Properties of Uranyl Fluoride
Abstract: Pure UO2F2 is made by reaction between anhydrous HF and pure UO3. Although it is difficult to prepare free of water, it is not very hygroscopic. Prolonged heating at 100-105 degrees releases 99.9% of the water in an aqueous solution; the rate of loss of water is very small after saturation is reached. X-ray diffraction data give a density of 6.2 for the solid. The density of a 1.004 M solution is 1.274; the density of a saturated solution (5.130 M) is 2.400. The densities of F-9 solutions have been calculated from the densities of ordinary aqueous solutions, and the values are compared graphically. Data on the solubility indicate that there is a small increase in the range 25-100 degrees. Recovery of pure F-9 from a solution is hampered by hydrolysis of U)2F2 to give HF. The HF may be held back by addition of UO3 or CaO; the use of the latter, however, makes more difficult the recovery of all the F-9. Molar conductivities of UO2F2 solutions at 25 degrees, as well as the specific conductivities of a 1 molar solution containing various concentrations of UO3, have been determined. The addition of UO3 lowers the conductivity. The low …
Date:
September 11, 1944
Creator:
Dean, G. R.
Object Type:
Report
System:
The UNT Digital Library