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UNT Libraries Government Documents Department - 2,100 Matching Results
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Interim Report of APPR Irradiation Test Program at MTR
Description:
It is the purpose of this memo to clarify and revise burnup calculations for the APPR irradiation program and to present a proposed irradiation schedule. the report will also be in the nature of a review of the program.
Date:
January 21, 1957
Creator:
Gross, E. E. & Schaffer, L. D.
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Report
Interim report on diamond-drilling exploration in the Bull Canyon district, Montrose and San Miguel counties, Colorado
Description:
This report sumarizes the results of the US geological survey exploration in the Bull Canyon district from October 1955 to April 1956
Date:
January 1957
Creator:
Wallace, Roberts M.
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Report
Interim report on tests simulating the transient response of individual process tubes to inadvertent plugging
Description:
Current Panellit protection procedures, termed instability limits, come from calculations based on steady state experiments. However, the actual conditions in a process tube following a plugging occurrence sufficient to cause unstable flow are transient rather than steady state, and cannot be determined with great precision except by transient state experimentation. As a result, a program was initiated by the thermal Hydraulics Operation of HLO to perform a series of transient heat transfer exp…
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Date:
May 24, 1957
Creator:
Batch, J. M.; Hesson, G. M.; Thorne, W. L. & Toyoda, K. G.
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Report
Interim report on the development of a plastic bonded explosive
Description:
The purpose of this work was to investigate the possibilities of producing a plastic bonded explosive having greater mechanical strength than that of presently existing plastic bonded explosives. This interim report details activities and progress through July 15, 1957.
Date:
July 15, 1957
Creator:
Archibald, P. B.
Item Type:
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Report
Interim report on the development of an epoxy resin bonded explosive
Description:
This report summarizes the work done to date on the development of an epoxy resin bonded explosive (HMX). The original target values have been satisfied and further investigations will be on a semi-pilot plant scale. The following characteristics have been determined on laboratory specimens. Compressive strength, 11-12,000 psi; sensitivity (50 % height) 31 cm; density, 1.81 gm/cc; vacuum stability (cc gas/gm/24 hrs at 100{degrees}C), .42 cc/gm.
Date:
August 19, 1957
Creator:
Archibald, P.
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Report
Internal performance of several auxiliary air inlets immersed in a turbulent boundary layer at Mach numbers of 1.3, 1.5, and 2.0
Description:
Internal performance of normal-shock rectangular, circular, and scoop inlets and of external-compression inlets experimentally obtained with varying immersion in a turbulent boundary layer. Recoveries varied from about 95 percent of theoretical in the free stream to 80 percent with complete immersion, while the corresponding mass flows were usually above 95 percent of theoretical. Turning of the flow through 10 degrees caused losses in pressure recovery of 0.03 to 0.07. External compression did…
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Date:
January 18, 1957
Creator:
Huff, Ronald G. & Anderson, Arthur R.
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Report
Internal Performance of Several Divergent-Shroud Ejector Nozzles with High Divergence Angles
Description:
From Summary: "Nine divergent-shroud ejector configurations were investigated to determine the effect of shroud divergence angle on ejector internal performance. Unheated dry air was used for both the primary and secondary flows. The decrease in the design-point thrust coefficient with increasing flow divergence angle (angle measured from primary exit to shroud exit) followed very closely a simple relation involving the cosine of the angle. This indicates that design-point thrust performance fo…
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Date:
October 2, 1957
Creator:
Trout, Arthur M.; Papell, S. Stephen & Povolny, John H.
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Report
Internal Performance of Two-Dimensional Wedge Exhaust Nozzles
Description:
Memorandum presenting an experimental investigation of four rectangular-throat two-dimensional wedge exhaust nozzles. Three of the nozzles were designed to conform to Prandtl-Meyer streamlines for pressure ratios of 5, 10, and 24, and a fourth, arbitrarily contoured, with a length less than that required for isentropic expansion, was designed for a pressure ratio of about 9.
Date:
February 28, 1957
Creator:
Beale, William T. & Povolny, John H.
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Report
The interrelated effects of engine rotor momentum and flight regime on the dynamic stability of high-performance aircraft
Description:
Report presenting a five-degree-of-freedom analysis of aircraft maneuvering stability, which showed that gyroscopic moments due to engine rotor momentum produced considerable rolling asymmetry for certain values of stability derivatives and flight conditions. Results regarding the altitude effects, Mach number effects, initial load factor, effective dihedral, static stability, roll velocity, and comparison with simplified longitudinal- and lateral-mode theory are provided.
Date:
April 17, 1957
Creator:
North, Warren J.
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Report
INTERSTITIAL COMPOUNDS OF IRRADIATED GRAPHITE
Description:
No Description Available.
Date:
March 1, 1957
Creator:
Hennig, G.R. & Montet, G.L.
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Report
Investigation at High Subsonic Speeds of the Effects of Various Horizontal Fuselage Forebody Fins on the Directional and Longitudinal Stability of a Complete Model Having a 45 Degree Sweptback Wing
Description:
Memorandum presenting an investigation conducted in the high-speed 7- by 10-foot tunnel of the effects of various horizontal fuselage forebody fins on the directional and longitudinal stability characteristics at high subsonic speeds of a complete model with a 45 degree sweptback wing mounted in a high position on the fuselage. The model wing had an aspect ratio of 4, a taper ratio of 0.30, and NACA 65A006 airfoil sections parallel to the free stream.
Date:
January 16, 1957
Creator:
Sleeman, William C., Jr.
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Report
Investigation at High Subsonic Speeds of the Static Longitudinal and Lateral Stability Characteristics of Two Canard Airplane Configurations
Description:
"The present investigation was conducted in the Langley high-speed 7-by 10-foot tunnel to determine the static longitudinal and lateral stability characteristics at high subsonic speeds of two canard airplane configurations previously tested at supersonic speeds. The Mach number range of this investigation extended from 0.60 to 0.94 and a maximum angle-of-attack range of -2deg to 24deg was obtained at the lowest test Mach number. Two wing plan forms of equal area were studied in the present tes…
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Date:
December 3, 1957
Creator:
Sleeman, William C., Jr.
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Report
Investigation at High Subsonic Speeds of the Use of Low Auxiliary Tail Surfaces Having Dihedral to Improve the Longitudinal and Directional Stability of a T-Tail Model at High Lift
Description:
Memorandum presenting an investigation of the use of low auxiliary horizontal-tail surfaces to alleviate the pitch-up tendency at high lift of an airplane configuration with a T-tail. The basic model had a wing with an aspect ratio of 3, a taper ratio of 0.143, and an unswept 80-percent chord line.
Date:
December 5, 1957
Creator:
Sleeman, William C., Jr.
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Report
An investigation at low speed of the flow over a simulated flat plate at small angles of attack using pitot-static and hot-wire probes
Description:
Report presenting results from pitot-static and hot-wire anemometer surveys at low speed of the flow over a thin, sharp-edge airfoil which simulated a flat plate. The primary purpose was to obtain detailed measurements of the flow associated with the so-called thin-airfoil type of stall. Results regarding the preliminary tests, pressure distributions, mean flow measurements, velocity fluctuation measurements, and observations and measurements of the flow in the immediate vicinity of the leading…
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Date:
March 1957
Creator:
Gault, Donald E.
Item Type:
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Report
An Investigation at Low Speed of the Spin Instability of Mortar-Shell Tails
Description:
An investigation was made in the Langley stability tunnel to study the influence of number of fins, fin shrouding, and fin aspect ratio on the spin instability of mortar-shell tail surfaces. It was found that the 12-fin tails tested spun less rapidly throughout the angle-of-yaw range than did the 6-fin tails and that fin shrouding reduced the spin encountered by a large amount.
Date:
June 19, 1957
Creator:
Bird, John D. & Lichtenstein, Jacob H.
Item Type:
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Report
Investigation at low speeds of deflectors and spoilers as gust alleviators on a model of the Bell X-5 airplane with 35 degree swept wings and on a high-aspect-ratio 35 degree swept-wing-fuselage model
Description:
Results of an investigation at low speeds to determine the gust-alleviation capabilities (reduction in lift-curve slope) of spoilers and deflectors on a 35 degree swept-wing model of high aspect ratio and on a 1/4-scale model of the X-5 airplane with 35 degree swept wings indicate that deflector and spoiler-deflector types of controls can be designed to provide considerable gust alleviation for a swept-wing airplane while still maintaining stability and control.
Date:
June 1957
Creator:
Croom, Delwin R. & Huffman, Jarrett K.
Item Type:
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Report
Investigation at Mach Numbers to 1.04 of Blade-Loading Characteristics of Two Full-Scale Three-Blade Supersonic Propellers Differing in Blade-Section Camber
Description:
Memorandum presenting total-pressure surveys made in the slipstreams of two full-scale three-blade supersonic propellers in the 16-foot transonic tunnel at Mach numbers up to 1.04 to determine the effects of camber on supersonic-propeller characteristics. The two propellers were similar except that one of them had symmetrical blade sections and the other had cambered blade sections and a slightly different pitch distribution. Over the complete range of the tests, the cambered propeller maintain…
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Date:
September 12, 1957
Creator:
Salters, Leland B., Jr.
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Report
Investigation at transonic speeds of deflectors and spoilers as gust alleviators on a 35 degree swept wing: transonic bump method
Description:
Report presenting an investigation in the high-speed 7- by 10-foot tunnel using the transonic bump method to determine the gust-alleviation capabilities of spoilers and deflectors when mounted on a 35 degree swept semispan wing with NACA 65A006 airfoil sections. Testing was conducted over a range of Mach numbers and angles of attack.
Date:
June 1957
Creator:
Croom, Delwin R. & Huffman, Jarrett K.
Item Type:
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Report
Investigation at transonic speeds of loading over a 30 degree sweptback wing of aspect ratio 3, taper ratio 0.2, and NACA 65A004 airfoil section mounted on a body
Description:
Report presenting the aerodynamic load characteristics for a wing-body combination for a range of Mach numbers and angles of attack. Two wings with the same dimensions but different types of construction (one of solid steel, one of plastic with an inner steel core) were tested. Results regarding flow studies, chordwise pressure distributions, spanwise load distributions, panel loads, center of loads, and twist distribution are provided.
Date:
September 26, 1957
Creator:
Arabian, Donald D.
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Report
Investigation at Transonic Speeds of the Effects of Inlet-Lip Sweep on the Internal-Flow Characteristics of a Semielliptical Air Inlet With an Inlet-Lip Stagger of 30 Degrees
Description:
Report presenting an investigation in the transonic blowdown tunnel to determine the effects of inlet-lip sweep angle on the internal-flow characteristics of a semielliptical scoop-type inlet with an inlet lip stagger of 30 degrees. the testing was performed at a range of Mach numbers and mass-flow ratios. Results regarding flow over the nose, total-pressure recovery at inlet, flow distortions at inlet, boundary-layer control, and inlet performance are presented.
Date:
July 23, 1957
Creator:
Trescot, Charles D., Jr.
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Report
Investigation of 70 percent trimethyl borate 30 percent methyl alcohol fuel mixture in a single J33 combustor and in a J33 turbojet engine
Description:
Report presenting an experimental investigation on a single turbojet engine combustor and on a turbojet engine using a fuel mixture of 70 percent trimethyl borate and 30 percent methyl alcohol. Results regarding the single combustor's deposition, combustion efficiency, ignition, temperature distribution, pressure drop and the engine operation are provided.
Date:
January 23, 1957
Creator:
Schafer, Louis J., Jr. & Hickel, Robert O.
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Report
Investigation of a 0.6 Hub-Tip Radius-Ratio Transonic Turbine Designed for Secondary-Flow Study 1: Design and Experimental Performance of Standard Turbine
Description:
Report presenting an investigation of a transonic turbine with a 0.6 hub-tip radius ratio in order to determine the effect of stator and rotor secondary flows on turbine performance. Results regarding the overall performance, stator exit surveys, and rotor exit surveys are provided.
Date:
January 9, 1957
Creator:
Rohlik, Harold E.; Wintucky, William T. & Scibbe, Herbert W.
Item Type:
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Report
Investigation of a 0.6 Hub-Tip Radius-Ratio Transonic Turbine Designed for Secondary-Flow Study 2 - Design and Experimental Performance of Turbine With Low-Velocity-Turning Stator and Standard Rotor
Description:
Memorandum presenting a low-velocity-turning stator designed to reduce secondary-flow loss cores by turning the flow at low velocities and accelerating it in passages of constant flow angle with reduced cross-channel pressure gradients. Performance of the stator was determined with static-pressure measurements and detailed surveys of total pressure and flow angle made with the turbine operating at design speed near design work.
Date:
July 18, 1957
Creator:
Rohlik, Harold E.; Wintucky, William T. & Scibbe, Herbert W.
Item Type:
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Report
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