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Technical Report Archive and Image Library
158
National Advisory Committee for Aeronautics Collection
81
Office of Scientific & Technical Information Technical Reports
41
TRAIL Microcard Collection
35
Texas Attorney General Opinions
32
Government Documents A to Z Digitization Project
1
Texas State Publications
1
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1
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233 Matching Results
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Incubation and brooding of chickens.
Describes the benefits of using artificial egg incubation and artificial brooding of chicks as economical ways to replace chicken flocks from year to year.
Date:
June 1953
Creator:
Olsen, Marlow William, 1906-
Object Type:
Book
System:
The UNT Digital Library
Comparison of Several Methods of Cyclic De-Icing of a Gas-Heated Airfoil
"Several methods of cyclic de-icing of a gas-heated airfoil were investigated to determine ice-removal characteristics and heating requirements. The cyclic de-icing system with a spanwise ice-free parting strip in the stagnation region and a constant-temperature gas-supply duct gave the quickest and most reliable ice removal. Heating requirements for the several methods of cyclic de-icing are compared, and the savings over continuous ice prevention are shown. Data are presented to show the relation of surface temperature, rate of surface heating, and heating time to the removal of ice" (p. 1).
Date:
June 22, 1953
Creator:
Gray, Vernon H. & Bowden, Dean T.
Object Type:
Report
System:
The UNT Digital Library
Altitude Performance of a 20-Inch-Diameter Ram-Jet Engine Investigated in a Free-Jet Facility at Mach Number 3.0
Report discussing the performance of a 20-inch-diameter ram-jet engine at Mach number 3.0 over a range of simulated altitudes from 60,500 to 66,500 feet. Information about the maximum combustor efficiency, range of exhaust-nozzle total pressures, lean blow-out, diffuser total-pressure recovery, and internal thrust coefficient is provided.
Date:
June 15, 1953
Creator:
Smolak, George R. & Wentworth, Carl B.
Object Type:
Report
System:
The UNT Digital Library
Effect of Ice and Frost Formations on Drag of NACA 65(sub 1) -212 Airfoil for Various Modes of Thermal Ice Protection
"The effects of primary and runback icing and frost formations on the drag of an 8-foot-chord NACA 651-212 airfoil section were investigated over a range of angles of attack from 20 to 80 and airspeeds up to 260 miles per hour for icing conditions with liquid-water contents ranging from 0.25 to 1.4 grams per cubic meter and datum air temperatures of -30 to 30 F. The results showed that glaze-ice formations, either primary or runback, on the upper surface near the leading edge of the airfoil caused large and rapid increases in drag, especially at datum air temperatures approaching 32 F and in the presence of high rates of water catch" (p. 1).
Date:
June 1953
Creator:
Gray, Vernon H. & von Glahn, Uwe H.
Object Type:
Report
System:
The UNT Digital Library
Procedure for Measuring Liquid-Water Content and Droplet Sizes in Supercooled Clouds by Rotating Multicylinder Method
"The rotating multicylinder method for in-flight determination of liquid-water content, droplet size, and droplet-size distribution in icing clouds is described. The theory of operation, the apparatus required, the technique of obtaining data in flight, and detailed methods of calculating the results, including necessary charts and tables, are presented" (p. 1).
Date:
June 29, 1953
Creator:
Lewis, William; Perkins, Porter J. & Brun, Rinaldo J.
Object Type:
Report
System:
The UNT Digital Library
Drag and Static Stability at Low Lift of Rocket-Powered Models of the Convair MX-1626 Airplane at Mach Numbers From 0.7 to 1.5
Report presenting flight testing on models of the proposed Consolidated Vultee Aircraft Corporation MX-1626 airplane with nacelles and without nacelles. Results regarding drag level, design modifications, dampening, trimming, and the use of ventral boosters are provided.
Date:
June 11, 1953
Creator:
Hall, James R. & Hopko, Russell N.
Object Type:
Report
System:
The UNT Digital Library
The Effects of Extensible Rocket Racks on Lift, Drag, and Stability of a 1/10 Scale Rocket-Boosted Model of the McDonnell XF3H-1 Airplane for a Mach Number Range of 0.60 to 1.34
Report presenting testing of the transonic longitudinal characteristics of a model of the McDonnell XF3H-1 airplane. The model had a center-of-gravity location of 28.5 percent of the mean aerodynamic chord and a stabilizer setting of -5.91 degrees relative to the wing chord plane with extensible rocket racks. Results regarding Reynolds number, rocket-rack program, flight time history, trim, lift, drag, longitudinal stability, directional stability, and inlet pressure recovery are provided.
Date:
June 16, 1953
Creator:
Crabill, Norman L.
Object Type:
Report
System:
The UNT Digital Library
Propeller-noise charts for transport airplanes
Report presenting calculations of rotational-noise and vortex-noise levels at a distance of 300 feet for engine ratings of 1000 to 10,000 horsepower for a large number of propellers in static operation. The results are presented in chart and table form for rapid estimation of the noise levels and spectrums in a range of tip Mach numbers. Results regarding tip Mach number, number of blades, and power loading are provided.
Date:
June 1953
Creator:
Hubbard, Harvey H.
Object Type:
Report
System:
The UNT Digital Library
The Condensation Line of Air and the Heats of Vaporization of Oxygen and Nitrogen
"The condensation pressure of air was determined over the range of temperature from 60 to 85 K. The experimental results were slightly higher than the calculated values based on the ideal solution law. Heat of vaporization of oxygen was determined at four temperatures ranging from about 68 to 91 K and of nitrogen similarly at four temperatures ranging from 62 to 78 K" (p. 1).
Date:
June 1953
Creator:
Furukawa, George T. & McCoskey, Robert E.
Object Type:
Report
System:
The UNT Digital Library
Physical Properties of Concentrated Nitric Acid
Note presenting a review of the data existing in the literature and experimental measurements made in order to obtain the physical properties of white fuming nitric acid. The main object of the investigation was to obtain reliable values of the thermal properties of concentrated nitric acid for use in correlating the data obtained in heat-transfer research and in fluid-friction-characteristics investigations.
Date:
June 1953
Creator:
Sibbitt, W. L.; St. Clair, C. R.; Bump, T. R.; Pagerey, P. F.; Kern, J. P. & Fyfe, D. W.
Object Type:
Report
System:
The UNT Digital Library
Creep-Buckling Analysis of Rectangular-Section Columns
Note presenting an extension of an analysis of the creep behavior of a slightly curved pin-ended H-section column under constant load to the slightly curved solid rectangular-section column. The analysis leads to a differential equation for the plastic strains at the midheight cross section.
Date:
June 1953
Creator:
Libove, Charles
Object Type:
Report
System:
The UNT Digital Library
Surveys of the flow fields at the propeller planes of six 40 degree sweptback wing-fuselage-nacelle combinations
Report presenting the flow fields at the propeller planes of six 40 degree sweptback semispan wing-fusleage-nacelle combinations to provide data and to enable the study of the characteristics of the flow fields and their effect on propeller-oscillating aerodynamic loads. Results regarding the propeller flow fields, oscillating aerodynamic loading, and upflow angles at the horizontal center lines of the propeller disks are provided.
Date:
June 1953
Creator:
Rogallo, Vernon L. & McCloud, John L., III
Object Type:
Report
System:
The UNT Digital Library
The Structure of Turbulence in Fully Developed Pipe Flow
Note presenting measurements made with a hot-wire anemometer in fully developed turbulent flow in a 10-inch pipe at speeds of approximately 10 and 100 feet per second. Emphasis was placed on turbulence and conditions near the wall. Results regarding the mean-energy balance, turbulent-energy balance, energy-spectrum considerations, and some general considerations are provided.
Date:
June 1953
Creator:
Laufer, John
Object Type:
Report
System:
The UNT Digital Library
A Method for Stabilizing Shock Waves in Channel Flow by Means of a Surge Chamber
Note presenting a method based on mass removal from the channel by means of a surge chamber in order to stabilize normal shock waves in channel flow against the effect of disturbances originating downstream in a blowdown-type wind tunnel. The results of experimental tests were in quantitative agreement with the theoretical analysis.
Date:
June 1953
Creator:
Neice, Stanford E.
Object Type:
Report
System:
The UNT Digital Library
Flight Investigation of the Effect of Transient Wing Response on Wing Strains of a Four-Engine Bomber Airplane in Rough Air
Report presenting a flight investigation on a four-engine bomber airplane to determine the effects of wing flexibility on wing strains developed in flight through clear-air turbulence. Amplification of the effects appeared to be a function of gust-gradient distance and was not significantly affected by airspeed or weight.
Date:
June 1953
Creator:
Murrow, Harold N. & Payne, Chester B.
Object Type:
Report
System:
The UNT Digital Library
Reaction processes leading to spontaneous ignition of hydrocarbons
Report presenting testing of the vapor-oxidation of iscooctane at 550 degrees Celsius under conditions leading to rapid quenching of the reaction yielding hydrogen peroxide, diiosbutylene, and isobutylene as the major reaction products. Results regarding isooctane, n-Heptane, 2,2,5-Trimethylhexane, isobutane, and hydrogen-peroxide formation are provided.
Date:
June 1953
Creator:
Frank, Charles E. & Blackham, Angus U.
Object Type:
Report
System:
The UNT Digital Library
Theoretical Investigation of the Supersonic Lift and Drag of Thin, Sweptback Wings With Increased Sweep Near the Root
Note presenting formulas derived by the use of linearized theory for the lift and drag due to lift, at supersonic speeds, of thin, flat wings with a discontinuity in the leading-edge sweep, the inboard portion of the leading-edge being very highly swept an the outboard portion less so. The lift-curve slope and drag have been calculated for several families of wings, all with straight trailing edges.
Date:
June 1953
Creator:
Cohen, Doris & Friedman, Morris D.
Object Type:
Report
System:
The UNT Digital Library
Drag of circular cylinders for a wide range of Reynolds numbers and Mach numbers
From Summary: "Pressure distributions around circular cylinders placed perpendicular to the stream for subsonic and supersonic flow conditions have been obtained. Drag coefficients calculated from these wind-tunnel tests and from transonic free-flight tests are presented. Drag data are presented for the Mach number range of 0.3 to 2.9."
Date:
June 1953
Creator:
Gowen, Forrest E. & Perkins, Edward W.
Object Type:
Report
System:
The UNT Digital Library
Subsonic Flow of Air Through a Single-Stage and a Seven-Stage Compressor
Note presenting a method for solving the steady flow of a non-viscous compressible fluid along a relative stream surface between two adjacent blades in a turbomachine that is applied to investigate the low- and high-speed subsonic air flow through a single-stage and through a seven-stage axial compressor. Comparisons of the design, flow, and air compressibility are provided.
Date:
June 1953
Creator:
Wu, Chung-Hua
Object Type:
Report
System:
The UNT Digital Library
Effect of Variation in Rivet Strength on the Average Stress at Maximum Load for Aluminum-Alloy, Flat, Z-Stiffened Compression Panels That Fail by Local Buckling
"A study is made of the effect of variation in rivet strength on the average panel stress at maximum load for 75S-T6 aluminum-alloy, flat, Z-stiffened compression panels that fail by local buckling. A curve is presented for the determination of the relationship between strength, diameter, and pitch of the rivets, and the strength of stiffened, flat compression panels of such proportions that failure is by local buckling" (p. 1).
Date:
June 1953
Creator:
Dow, Norris F.; Hickman, William A. & Rosen, B. Walter
Object Type:
Report
System:
The UNT Digital Library
A revised formula for the calculation of gust loads
"A revised gust-load formula with a new gust factor is derived to replace the gust-load formula and alleviation factor widely used in gust studies. The revised formula utilizes the same principles and retains the sample simple form of the original formula, but provides a more appropriate and acceptable basis for gust-load calculations. The gust factor is calculated on the basis of a one-minus-cosine gust shape and is presented as a function of a mass-ratio parameter in contrast to the ramp gust shape and wing loading, respectively, used in the alleviation factor" (p. 1).
Date:
June 1953
Creator:
Pratt, Kermit G.
Object Type:
Report
System:
The UNT Digital Library
A Small Pirani Gage for Measurements of Nonsteady Low Pressures
Note presenting a precise, stable, rapid-response Pirani gage that can be used to precisely measure low absolute pressures such as ones found in supersonic wind tunnels. A theoretical analysis of the gage is given and may be used as a guide in the design, application, and evaluation of such a gage.
Date:
June 1953
Creator:
Pilny, M. John
Object Type:
Report
System:
The UNT Digital Library
The Drag of Finite-Length Cylinders Determined From Flight Tests at High Reynolds Numbers for a Mach Number Range From 0.5 to 1.3
"Results of a free-flight investigation to determine the drag of circular, finite-length cylinders are presented for a Mach number range from about 0.5 to 1.3. Also included are drag results of previous experimental tests of infinite-length cylinders. Drag of circular cylinders at supersonic speeds is largely independent of fineness ratio and Reynolds number; whereas, at subsonic speeds, the drag of finite-length cylinders (fineness rations of about 60 and below) increases as their fineness ratios increase" (p. 1).
Date:
June 1953
Creator:
Welsh, Clement J.
Object Type:
Report
System:
The UNT Digital Library
The Galvanic Corrosion Theory for Adherence of Porcelain-Enamel Ground Coats to Steel
Note presenting an investigation of the galvanic corrosion theory of adherence between ground-coat porcelain enamels and steel as part of a broad study of the bonding mechanism between ceramics and metals. The theory is based on the mechanical anchoring of the enamel into the pits formed by the galvanic attack of the enamel on the steel surface.
Date:
June 1953
Creator:
Moore, D. G.; Pitts, J. W.; Richmond, J. C. & Harrison, W. N.
Object Type:
Report
System:
The UNT Digital Library