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  Partner: UNT Libraries Government Documents Department
 Decade: 1950-1959
 Year: 1957
 Month: April
 Collection: Technical Report Archive and Image Library
15 MW Gas-Cooled Closed-Cycle Reactor Power System Study: Final Report, Volumes 1-2

15 MW Gas-Cooled Closed-Cycle Reactor Power System Study: Final Report, Volumes 1-2

Date: April 1, 1957
Creator: unknown
Description: This report covers a feasibility study for a 15 megawatt gas cooled reactor power system, conducted by the Ford Instrument Company Division of the Sperry Rand Corporation during the months of March to August 1956.
Contributing Partner: UNT Libraries Government Documents Department
Altitude performance of pentaborane - JP-4 fuel blends in a modified J47 combustor

Altitude performance of pentaborane - JP-4 fuel blends in a modified J47 combustor

Date: April 17, 1957
Creator: Branstetter, J Robert & Kaufman, Warner B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Analysis of static aeroelastic behavior of low-aspect-ratio rectangular wings

Analysis of static aeroelastic behavior of low-aspect-ratio rectangular wings

Date: April 1, 1957
Creator: Hedgepeth, John M & Waner, Paul G , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Boundary-Layer-Transition and Heat-Transfer Measurements from Flight Tests of Blunt and Sharp 50 Degree Cones at Mach Numbers from 1.7 to 4.7

Boundary-Layer-Transition and Heat-Transfer Measurements from Flight Tests of Blunt and Sharp 50 Degree Cones at Mach Numbers from 1.7 to 4.7

Date: April 18, 1957
Creator: Chauvin, Leo T. & Speegle, Katherine C.
Description: Boundary-layer-transition and heat-transfer measurements were obtained from flight tests of blunt and sharp cones having apex angles of 50 deg. The test Mach number range was from 1.7 to 4.7, corresponding to free-stream Reynolds numbers, based on cone base diameter, of 18. 3 x 10(exp 6) and 32.1 x 10(exp 6), respectively. Transition on both models occurred at a local Reynolds number of 1 x 10(exp 6) to 2 X 10(exp 6) based on distance from the stagnation point. Transition Reynolds numbers based on momentum thickness were between 320 and 380 for the blunt cone. The model surface roughness was 25 rms microinches or greater. Turbulent heat transfer to the conical surface of the blunt cone at a Mach number of 4 was 30 percent less than that to the surface of the sharp cone. Available theories predicted heat-transfer coefficients reasonably well for the fully laminar or turbulent flow conditions.
Contributing Partner: UNT Libraries Government Documents Department
Brookhaven National Laboratory Annual Report: July 1, 1956

Brookhaven National Laboratory Annual Report: July 1, 1956

Date: April 1957
Creator: Brookhaven National Laboratory
Description: Report issued by the Brookhaven National Laboratory discussing the work conducted by the lab during the fiscal year of 1956. As stated in the introduction, "the progress and trends of the research program are presented along with a description of the operational, service, and administrative activities of the Laboratory" (p. vii). This report includes tables, illustrations, and photographs.
Contributing Partner: UNT Libraries Government Documents Department
Bursting strength of unstiffened pressure cylinders with slits

Bursting strength of unstiffened pressure cylinders with slits

Date: April 1, 1957
Creator: Peters, Roger W & Kuhn, Paul
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A collection of data for zero-lift damping in roll of wing-body combinations as determined with rocket-powered models equipped with roll-torque nozzles

A collection of data for zero-lift damping in roll of wing-body combinations as determined with rocket-powered models equipped with roll-torque nozzles

Date: April 1, 1957
Creator: Stone, David G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Component performance investigation of J71 experimental turbine IX : effect of first-stator adjustment;internal flow conditions of J71-97 turbine with 87-percent-design stator area

Component performance investigation of J71 experimental turbine IX : effect of first-stator adjustment;internal flow conditions of J71-97 turbine with 87-percent-design stator area

Date: April 30, 1957
Creator: Schum, Harold J; Petrash, Donald A & Davison, Elmer H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Condition Surveys of Pavements Subjected to Channelized Traffic: Report 1, Davis-Monthan Air Force Base, Tucson, Arizona

Condition Surveys of Pavements Subjected to Channelized Traffic: Report 1, Davis-Monthan Air Force Base, Tucson, Arizona

Date: April 1957
Creator: Waterways Experiment Station (U.S.)
Description: Preface: The purpose of this report is to present the results of a condition survey performed on taxiway 14, Davis-Monthan Air Force Base, in accordance with addendum 6 to Instructions and Outline, "Condition Survey for Existing Pavements."
Contributing Partner: UNT Libraries Government Documents Department
A Convenient Table for Determining Metastable Transitions in Mass Spectra

A Convenient Table for Determining Metastable Transitions in Mass Spectra

Date: April 1957
Creator: Meyer, R. A. & Earnshaw, D. G.
Description: Report issued by the Bureau of Mines on a table developed for determining metastable transitions. The table is presented. This report includes tables, and illustrations.
Contributing Partner: UNT Libraries Government Documents Department
Copper Mines and Prospects Adjacent to Landlocked Bay, Prince William Sound, Alaska

Copper Mines and Prospects Adjacent to Landlocked Bay, Prince William Sound, Alaska

Date: April 1957
Creator: Mihelich, Miro & Wells, R. R.
Description: Report issued by the Bureau of Mines over explorations to find prospective copper mines near Valdez, Alaska. The results of the explorations are presented. This report includes tables, maps, and illustrations.
Contributing Partner: UNT Libraries Government Documents Department
Dynamic longitudinal stability characteristics of a swept-wing fighter-type airplane at Mach numbers between 0.36 and 1.45

Dynamic longitudinal stability characteristics of a swept-wing fighter-type airplane at Mach numbers between 0.36 and 1.45

Date: April 1, 1957
Creator: Wolowicz, Chester H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of an interface on transient temperature distribution in composite aircraft joints

Effect of an interface on transient temperature distribution in composite aircraft joints

Date: April 1, 1957
Creator: Barzelay, Martin E & Holloway, George F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of fuselage length and a canopy on the static longitudinal and lateral stability characteristics of 45 degrees sweptback airplane models having fuselages with square cross sections

Effect of fuselage length and a canopy on the static longitudinal and lateral stability characteristics of 45 degrees sweptback airplane models having fuselages with square cross sections

Date: April 1, 1957
Creator: Jaquet, Byron M & Fletcher, H S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Effect of Solid Admixtures on the Velocity of Motion of a Free Dusty Air Jet

The Effect of Solid Admixtures on the Velocity of Motion of a Free Dusty Air Jet

Date: April 1, 1957
Creator: Chernov, A. P.
Description: In dusty air flows occurring in industrial practice in transport by air pressure of friable materials, in the drying, annealing, and so forth, of a pulverized solid mass in suspension, and in other processes, the concentration of solid particles usually has a magnitude of the order of 1 kg per 1 kg of air. At such a concentration, the ratio of the volume of the particles to the volume of the air is small (less than one-thousandth part). However, regardless of this, the presence of a solid admixture manifests itself in the rules for the velocity distribution of the air in a dusty air flow. As a result, the rules of velocity change are different for clean and for dusty air flows. The estimation of the influence of the admixture on the velocity of the motion of the flow presents a definitive interest. One of the attempts to estimate that influence on the axial velocity of a free axially symmetrical jet with admixtures was made by Abramovich. Abramovich assumed beforehand that the fine particles of the admixture in the jet are subject to the motion of the air (that is, that the velocity of the admixture is approximately equal to ...
Contributing Partner: UNT Libraries Government Documents Department
Effect of spanwise variations in gust intensity on the lift due to atmospheric turbulence

Effect of spanwise variations in gust intensity on the lift due to atmospheric turbulence

Date: April 1, 1957
Creator: Diederich, Franklin W & Drischler, Joseph A
Description: The effect of spanwise variations in gust intensity on the power spectrum directly due to atmospheric turbulence is calculated for several analytic approximations to the correlation function or power spectra of atmospheric turbulence, for several spanwise weighing functions (span loadings), and for various angles of sweepback.
Contributing Partner: UNT Libraries Government Documents Department
Effects of Inlet Modification and Rocket-Rack Extension on the Longitudinal Trim and Low-Lift Drag of the Douglas F5D-1 Airplane as Obtained with a 0.125-Scale Rocket-Boosted Model between Mach Numbers of 0.81 and 1.64, TED No. NACA AD 399

Effects of Inlet Modification and Rocket-Rack Extension on the Longitudinal Trim and Low-Lift Drag of the Douglas F5D-1 Airplane as Obtained with a 0.125-Scale Rocket-Boosted Model between Mach Numbers of 0.81 and 1.64, TED No. NACA AD 399

Date: April 19, 1957
Creator: Hastings, Earl C., Jr. & Dickens, Waldo L.
Description: A flight investigation was conducted to determine the effects of an inlet modification and rocket-rack extension on the longitudinal trim and low-lift drag of the Douglas F5D-1 airplane. The investigation was conducted with a 0.125-scale rocket-boosted model which was flight tested at the Langley Pilotless Aircraft Research Station at Wallops Island, Va. Results indicate that the combined effects of the modified inlet and fully extended rocket racks on the trim lift coefficient and trim angle of attack were small between Mach numbers of 0.94 and 1.57. Between Mach numbers of 1.10 and 1.57 there was an average increase in drag coefficient of about o,005 for the model with modified inlet and extended rocket racks. The change in drag coefficient due to the inlet modification alone is small between Mach numbers of 1.59 and 1.64.
Contributing Partner: UNT Libraries Government Documents Department
Evaluation of several ram-jet combustor configurations using pentaborane fuel

Evaluation of several ram-jet combustor configurations using pentaborane fuel

Date: April 1, 1957
Creator: Sheldon, John W & Cervenka, A J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Expected numbers of maxima and minima of a stationary random process with non-Gaussian frequency distribution

Expected numbers of maxima and minima of a stationary random process with non-Gaussian frequency distribution

Date: April 1, 1957
Creator: Diederich, Franklin W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental determination at subsonic speeds of the oscillatory and static lateral stability derivatives of a series of delta wings with leading-edge sweep from 30 to 86.5 degrees

Experimental determination at subsonic speeds of the oscillatory and static lateral stability derivatives of a series of delta wings with leading-edge sweep from 30 to 86.5 degrees

Date: April 12, 1957
Creator: Letko, William
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An experimental hydrodynamic investigation of the inception of vortex ventilation

An experimental hydrodynamic investigation of the inception of vortex ventilation

Date: April 1, 1957
Creator: Ramsen, John A
Description: Results are presented from a hydrodynamic investigation of the inception of vortex ventilation on modified-flat-plate rectangular lifting surfaces of aspect ratio 0.25 differing in scale and thickness ratio. Two types of bubble-formation processes are described. Inception speeds were correlated for bubble formation in the high angle-of-attack range by using the Froude number and for that in the low angle-of-attack range by expressing the speed as a function of the thickness ratio.
Contributing Partner: UNT Libraries Government Documents Department
Experimental investigation of performance of single-stage transonic compressor with guide vanes turning counter to direction of rotor whirl

Experimental investigation of performance of single-stage transonic compressor with guide vanes turning counter to direction of rotor whirl

Date: April 22, 1957
Creator: Jahnsen, Lawrence J & Fessler, Theodore E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental performance of a 5000-pound- thrust rocket chamber using a 20-percent- fluorine - 80-percent-oxygen mixture with RP-1

Experimental performance of a 5000-pound- thrust rocket chamber using a 20-percent- fluorine - 80-percent-oxygen mixture with RP-1

Date: April 24, 1957
Creator: Kutina, F. J., Jr.; Rothenberg, E. A. & Tomazic, W. A.
Description: Increased performance of rocket engine using fluorine-oxygen mixture with RP-1 fuel.
Contributing Partner: UNT Libraries Government Documents Department
Experimental performance of a 5000-pound-thrust rocket chamber using a 20-percent-fluorine -80-percent-oxygen mixture with RP-1

Experimental performance of a 5000-pound-thrust rocket chamber using a 20-percent-fluorine -80-percent-oxygen mixture with RP-1

Date: April 24, 1957
Creator: Tomazic, William A; Kutina, Franklin J , Jr & Rothenberg, Edward A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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