UNT Libraries Government Documents Department - 32 Matching Results

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Comparison of theoretical and experimental zero-lift drag-rise characteristics of wing-body-tail combinations near the speed of sound

Description: Report presenting the zero-lift drag rise at low supersonic speeds computed by linearized theory for several wing-body-tail combinations and a comparison with experimental data. The results indicate that the computation method is capable of computing the drag rise at low supersonic speeds to an accuracy of about 20 percent.
Date: October 16, 1953
Creator: Holdaway, George H.
Item Type: Refine your search to only Report
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Damping in Yaw and Static Directional Stability of a Canard Airplane Model and of Several Models Having Fuselages of Relatively Flat Cross Section

Description: Report presenting an investigation to determine the damping in yaw and static directional stability characteristics for a flat-fuselage model with its major cross-sectional axis either horizontal or vertical, for a flat-fuselage model with its major axis horizontal in combination with a 45 degree sweptback wing, and for a canard model with a triangular control surface and 45 degree sweptback wing.
Date: October 16, 1950
Creator: Johnson, Joseph L.
Item Type: Refine your search to only Report
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Detail Calculations of the Estimated Shift in Stick-Fixed Neutral Point Due to the Windmilling Propeller and to the Fuselage of the Republic XF-12 Airplane

Description: "Detail calculations are presented of the shifts in stick-fixed neutral point of the Republic XF-12 airplane due to the windmilling propellers and to the fuselage. The results of these calculations differ somewhat from those previously made for this airplane by Republic Aviation Corporation personnel under the direction of Langley flight division personnel. Due to these differences the neutral point for the airplane is predicted to be 37.8 percent mean aerodynamic chord, instead of 40.8 percentā€¦ more
Date: October 16, 1944
Creator: White, M. D.
Item Type: Refine your search to only Report
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Effect of Geometry on Secondary Flows in Blade Rows

Description: Memorandum presenting an investigation of the influence of blade-row geometry on secondary flows in a two-dimensional cascade by varying independently stagger angle, aspect ratio, solidity, and angle of attack and by providing blade fillets. Stagger angle and aspect ratio had no appreciable effect on this secondary flow, whereas solidity and angle of attack did affect the flow patterns indicating the turning as a major parameter.
Date: October 16, 1952
Creator: Hansen, A. G.; Costello, G. R. & Herzig, H. Z.
Item Type: Refine your search to only Report
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Experimental investigation of effects of simulated nacelles and wing-root freedoms on supersonic flutter characteristics of a cambered, modified, swept, tapered wing

Description: Report presenting an investigation to determine the effects of simulated engine nacelles and wing-root freedoms on the flutter characteristics of a cambered, modified, swept, tapered, semispan wing through a range of Mach numbers. Wings were tested with and without nacelles and with the model restrained, free to roll, and free to translate in the vertical direction. Results regarding the effect of nacelles, flutter boundary, and effect of wing-mount freedom are provided.
Date: October 16, 1957
Creator: Hanson, Perry W.
Item Type: Refine your search to only Report
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Experimental investigation of effects of simulated nacelles and wing-root freedoms on supersonic flutter characteristics of a cambered, modified, swept, tapered wing

Description: Report presenting an experimental investigation made in the supersonic flutter tunnel to determine the effects of simulated engine nacelles and wing-root freedoms on the flutter characteristics of a cambered, modified, swept, tapered, semispan wing over a range of Mach numbers. Results regarding the effect of nacelles, flutter boundary, and effect of wing-mount freedom are provided.
Date: October 16, 1957
Creator: Hanson, Perry W.
Item Type: Refine your search to only Report
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A Flight and Analog Study of the Effect of Elevating the Radar-Boresight Axis Upon Stability and Tracking Performance of an Automatically Controlled Interceptor

Description: Report presenting flight and analog-simulator tests with a prototype automatic interceptor in order to study the effects of elevating the radar-boresight axis on the stability and tracking performance of the system. Results regarding effects of interceptor rolling motion upon tracking errors, similarity of flight results and analog-computer results, effect of elevating the radar-boresight axis upon stability, effect of elevating the radar-boresight axis upon the required bank-angle feedback, anā€¦ more
Date: October 16, 1957
Creator: Cheatham, Donald C. & Mathews, Charles W.
Item Type: Refine your search to only Report
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A Flight and Analog Study of the Effect of Elevating the Radar-Boresight Axis Upon Stability and Tracking Performance of an Automatically Controlled Interceptor

Description: Report presenting flight and analog-simulator tests with a prototype automatic interceptor in order to study the effects of elevating the radar-boresight axis on the stability and tracking performance of the system. The interceptor was designed to perform the lead-pursuit type of attacks and test runs were made in flight and on the analog simulator with and without lead-angle computation. Results regarding the effects of interceptor rolling motion upon tracking errors, similarity of flight resuā€¦ more
Date: October 16, 1957
Creator: Cheatham, Donald C. & Mathews, Charles W.
Item Type: Refine your search to only Report
open access

The Forces and Pressure Distribution at Subsonic Speeds on a Plane Wing Having 45 Degrees of Sweepback, an Aspect Ratio of 3, and a Taper Ratio of 0.5

Description: Memorandum presenting an investigation to determine the effects of scale and compressibility on the forces, moments, and pressure distribution on a wing with an aspect ratio of 3 and a taper ratio of 0.5. Lift, drag, and pitching-moment data and the chordwise distribution of static pressure at seven spanwise stations are presented for several sets of Reynolds and Mach numbers. The results indicated that for all Mach and Reynolds numbers in the test range, no apparently flow separation existed nā€¦ more
Date: October 16, 1951
Creator: Kolbe, Carl D. & Boltz, Frederick W.
Item Type: Refine your search to only Report
open access

FORE - A Computational Program For The Analysis Of Fast Reactor Excursions

Description: A digital computer program, FORE, which calculates transients for a fast reactor, has been coded for the TRANSAC 2000 computer. Its purpose is to provide understanding of the dynamics of fast reactors with particular emphasis on large ceramic-fueled fast reactors. The program calculates reactor power and temperatures of fuel, coolant, clad, and structure.
Date: October 16, 1962
Creator: Greebler, P.; Sherer, D. B. & Walton, N. H.
Item Type: Refine your search to only Report
open access

Free-Jet Investigation of a 20-Inch Ram-Jet Combustor Utilizing High-Heat-Release Pilot Burner

Description: Report presenting an investigation of the performance of a 20-inch-diameter ramjet engine with a high-heat-release pilot burner conducted at zero angle of attack in a free-jet test facility at a Mach number of 3.0. Two flame-holder configurations were used in conjunction with the high-heat-release pilot burner over a range of altitudes. Results regarding the performance of the high-heat-release pilot burner and performance of combustion-chamber configurations are provided.
Date: October 16, 1953
Creator: Henzel, James G., Jr. & Wentworth, Carl B.
Item Type: Refine your search to only Report
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III. Crystalline Complexes of Bis(Di-2-Ethylbutylphosphinyl) Methahe With Uranium(VI) Nitrate and With Thorium Nitrate

Description: Technical report. From Abstract : "Bis(di-2-ethylbutylphosphinyl)methane, EBDPM, forms complexes with uranium (VI) nitrate and thorium (IV) nitrate in which EBDPM acts as a bidentate ligand and the nitrato groups appear to be coordinated. The complex with uranium (VI) is a monomer, UO2(NO3)29EBDPM), while the complex with thorium in a dimer, [Th(NO3)4]2(EBDPM)3. Both complexes are of high thermal stability."
Date: October 16, 1962
Creator: Parker, James R. & Banks, Charles V.
Item Type: Refine your search to only Report
open access

Inelastic Column Behavior

Description: The significant findings of a theoretical study of column behavior in the plastic stress range are presented. When the behavior of a straight column is regarded as the limiting behavior of an imperfect column as the initial imperfection (lack of straightness) approaches zero, the departure from the straight configuration occurs at the tangent-modulus load. Without such a concept of the behavior of a straight column, one is led to the unrealistic conclusion that lateral deflection of the column ā€¦ more
Date: October 16, 1950
Creator: Duberg, John E. & Wilder, Thomas W., III
Item Type: Refine your search to only Report
open access

Integrals and Integral Equations in Linearized Wing Theory

Description: "The formulas of subsonic and supersonic wing theory for source, doublet, and vortex distributions are reviewed and a systematic presentation is provided which relates these distributions to the pressure and to the vertical induced velocity in the plane of the wing. It is shown that care must be used in treating the singularities involved in the analysis and that the order of integration is not always reversible. Concepts suggested by the irreversibility of order of integration are shown to be ā€¦ more
Date: October 16, 1950
Creator: Lomax, Harvard; Heaslet, Max A. & Fuller, Franklyn B.
Item Type: Refine your search to only Report
open access

Organic Continuous Cartridge for the Purex 2D Column

Description: This document covers work done in 3- and 4-inch-diameter glass columns directed toward the development of improved cartridges for the Purex Plant final uranium cycle extraction column, the 2D column. A nozzle plate cartridge for the extraction section and a mixed plate cartridge containing both stainless steel and fluorothene sieve plates for the scrub section were developed. In 3- and 4-inch-diameter glass columns these cartridges have a uranium extraction efficiency as good as or better than ā€¦ more
Date: October 16, 1956
Creator: Hesson, G. M.
Item Type: Refine your search to only Report
open access

Performance characteristics at Mach numbers to 2.0 of various types of side inlets mounted on fuselage of proposed supersonic airplane 3: normal wedge inlet with semicircular cowl

Description: Report presenting an investigation of inlets utilizing two-dimensional compression wedges mounted normal to the fuselage surface with ram-type scoops for partial removal of the boundary layer. Two compression-wedge angles were included to simulate fixed positions of a variable-geometry configuration. Results regarding supersonic performance characteristics and subsonic and take-off performance characteristics are provided.
Date: October 16, 1952
Creator: Esenwein, Fred T.
Item Type: Refine your search to only Report
open access

A preliminary investigation of methods for improving the pressure recovery characteristics of variable-geometry supersonic-subsonic diffuser systems

Description: Report presenting an investigation to study methods for improving the pressure-recovery characteristics of two-dimensional, variable-geometry, supersonic-subsonic diffuser systems. Results without injection, with injection, and effect of diffuser configuration on wind-tunnel performance are provided.
Date: October 16, 1957
Creator: Hasel, Lowell E. & Sinclair, Archibald R.
Item Type: Refine your search to only Report
open access

Radiative Capture of Protons in NeĀ²ā°

Description: Abstract: "A preliminary measurement of the NeĀ²ā°(p,Ī³)NaĀ²Ā¹ reaction cross section has been made. Targets were prepared by bombarding aluminum targets with neon ions. The neon concentration in the target was determined by elastic scattering of 1.5-Mev-protons. The yield of positrons from the reaction NeĀ²ā°(p,Ī³)NaĀ²Ā¹(Ī²)NeĀ²Ā¹ was identified by the 23-second half life of NaĀ²Ā¹."
Date: October 16, 1957
Creator: Pixley, R. E.; Hester, R. E. & Lamb, W. A. S.
Item Type: Refine your search to only Report
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