UNT Libraries Government Documents Department - 262 Matching Results

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The Absorption and Translocation of Several Fission Elements by Russian Thistle

Description: Abstract: An investigation was conducted to determine the absorption and translocation of fission products by Russian thistle from a localized spot of contaminated soil. The amount and identity of the radioactive elements absorbed and translocated by the Russian thistle is given along with the location of these elements in the plants. Beta radioactivity to the amounts of 10 microcuries per gram caused no visible effects on the growth habits of sectioned material are included.
Date: June 8, 1950
Creator: Selders, A. A.

Acceleration Characteristics of R-3350 Engine Equipped with NACA Injection Impeller

Description: From Summary: "Qualitative investigations have shown that use of the NACA injection impeller with the R-3350 engine increases the inertia of the fuel-injection system and, when the standard fuel-metering system is used, this increase in inertia results in poor engine acceleration characteristics. This investigation was therefore undertaken to determine whether satisfactory acceleration characteristics of the engine equipped with the injection impeller could be obtained by simple modifications to the fuel-monitoring system. The engine was operated with two types of carburetor; namely, a hydraulic-metering carburetor incorporating a vacuum-operated accelerating pump and a direct-metering carburetor having a throttle-actuated accelerating pump."
Date: January 8, 1947
Creator: Hickel, Robert O. & Snider, William E.

Aerial Radiometric and Magnetic Survey: Beeville/Bay City National Topographic Map, Texas Gulf Coast, Volume 1

Description: Final report documenting a high-sensitivity airborne gamma radiation and magnetic field survey of the Texas portions of the Beeville (NH 14-12 quadrangle) and Bay City (NH 15-10 quadrangle) National Topographic Map segments including a description of the program and results.
Date: January 8, 1979
Creator: Bendix Field Engineering Corporation. Grand Junction Operations.
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Aerodynamic characteristics of a wing with unswept quarter-chord line, aspect ratio 2, taper ratio 0.78, and NACA 65A004 airfoil section: transonic-bump method

Description: From Introduction: "This paper presents the results of an investigation of force and moment characteristics for a wing with an unswept quarter-chord line, aspect ratio 2, taper ratio 0.78, and an NACA 65A004 airfoil section parallel to the free stream."
Date: March 8, 1950
Creator: Polhamus, Edward C. & Campbell, George S.

Aerodynamic characteristics of a wing with unswept quarter-chord line, aspect ratio 4, taper ratio 0.6, and NACA 65A004 airfoil section: Transonic-bump method

Description: From Introduction: "This paper presents the results of the investigation of the wing alone and of the wing-fuselage configurations employing a wing with an unswept quarter-chord line, aspect ratio 4, taper ratio 0.6, and an NACA 65A004 airfoil section parallel to the air stream. The experimental results of a wing of identical plan from having an NACA 65A006 airfoil section which was tested as part of the transonic program are presented in reference 1.
Date: May 8, 1950
Creator: Myers, Boyd C., II & Wiggins, James W.

Aerodynamic Investigation of a Parabolic Body of Revolution at Mach Number of 1.92 and Some Effects of an Annular Jet Exhausting From the Base

Description: Report discussing an investigation of a parabolic body of revolution with and without the effects of an annular jet exhausting from the base. The aerodynamic characteristics, pressures, lift-curve slope, and other characteristics with the jet in operation and inoperative were compared.
Date: February 8, 1950
Creator: Love, Eugene S.

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : effectiveness of an elevon as a longitudinal control and the effects of camber and twist on the maximum lift-drag ratio at supersonic speeds

Description: Report presenting an investigation concerned with the measurement of the characteristics of longitudinal-control devices for a wing-fuselage combination with a wing with the leading edge swept back 63 degrees. Most of the investigation was devoted to testing a 30-percent-chord, 50-percent-semispan elevon, but some used upper-surface spoilers. Results regarding the characteristics of the wing with the elevon undeflected and control-surface effectiveness are provided.
Date: May 8, 1950
Creator: Olson, Robert N. & Mead, Merrill H.

Aerodynamics of slender bodies at Mach number of 3.12 and Reynolds numbers from 2 x 10(exp 6) to 15 x 10(exp 6) 2: aerodynamic load distributions of series of five bodies having conical noses and cylindrical afterbodies

Description: Report presenting an experimental investigation to determine the aerodynamic load distributions of a series of five bodies with conical or slightly blunted noses and cylindrical afterbodies in the 1- by 1-foot supersonic wind tunnel. Pressure distributions and viscous drags were measured at Mach number 3.12 for a range of Reynolds numbers and angles of attack.
Date: May 8, 1952
Creator: Jack, John R. & Gould, Lawrence I.

Air Sampling Chamber for S.I.R.

Description: Abstract: An ionization chamber to monitor air for beta activity is described. Operating curves are given, as well as results of shock and vibration tests. Recommendation for improved design are included.
Date: August 8, 1952
Creator: Dewes, R. A. & Goodale, E. E.

Air-Stream Surveys in the Vicinity of the Tail of a 1/8.33-Scale Powered Model of the Republic XF-12 Airplane

Description: "The XF-12 airplane was designed by Republic Aviation Corporation to provide the Army Air Forces with a high performance, photo reconnaissance aircraft. A series of air-stream surveys were made n the vicinity of the empennage of a 1/8.33-scale powered model of the XF-12 airplane in the Langley 19-foot pressure tunnel. Surveys of the vortical-tail region were made through a range of yaw angles of plus or minus 20 degrees at a high and low angle of attack" (p. 1).
Date: April 8, 1947
Creator: Foster, Gerald V.

Altitude operational characteristics of a prototype model of the J47D (RX1-1 and RX1-3) turbojet engines with integrated electronic control

Description: Report presenting an investigation of the altitude operational characteristics of a prototype model of the J47D turbojet engines, which includes an afterburner, a variable-area exhaust nozzle, and an integrated electronic control in an altitude wind tunnel. Results regarding compressor stall, compressor unstall, combustor blow-out during acceleration, stall and blow-out protection, acceleration characteristics, deceleration characteristics, and altitude starting characteristics, afterburner operational characteristics are provided.
Date: January 8, 1952
Creator: Bloomer, Harry E.; Conrad, E. William & Sobolewski, Adam E.

Altitude performance and operational characteristics of 29-inch-diameter tail-pipe burner with several fuel systems and flame holders on J35 turbojet engine

Description: From Summary: "An investigation of turbojet-engine thrust augmentation by means of tail-pipe burning has been conducted in the NACA Lewis altitude wind tunnel. Several fuel systems and flame holders were investigated in a 29-inch-diameter tail-pipe burner to determine the effect of fuel distribution and flame-holder design on tail-pipe-burner performance and operational characteristics over a range of simulated flight conditions. At an altitude of 5000 feet, the type of flame holder used had only a slight effect on the combustion efficiency."
Date: November 8, 1949
Creator: Conrad, E. William & Prince, William R.

Altitude Performance of AN-F-58 Fuels in British Rolls-Royce Nene Single Combustor

Description: "An investigation was conducted with a single combustor from a British Rolls-Royce Nene turbojet engine to determine the altitude performance characteristics of AN-F-58 fuels. Three fuel blends conforming to AN-F-58 specifications were prepared in order to determine the influence of fuel boiling temperatures and aromatic content on combustion efficiencies and altitude operational limits. The performance of the three AN-F-58 fuels was compared in the range of altitudes from sea level to 65,000 feet, engine speeds from 40- to 100- percent normal rated, and flight Mach numbers of 0.0 and 0.6" (p. 1).
Date: July 8, 1949
Creator: Cook, William P. & Koch, Richard G.

An analysis of the transonic and supersonic performance of several fixed-geometry air inlets

Description: Report presenting an analysis of the maximum power thrust-minus-drag performance of several turbojet-engine air-inlet combinations over a wide range of flight conditions. The primary objective of the analysis was to use the experimentally determined drag and total-pressure-recovery characteristics to show the range of satisfactory performance of each of several fixed-geometry inlet configurations. Results regarding the performance at 35,000 feet, inlet design considerations, speed range of efficient normal-shock inlet performance, effect of altitude on performance of the fixed-geometry system, and effect of nonstandard air on the performance of a fixed-geometry system are provided.
Date: March 8, 1955
Creator: Pendley, Robert E. & Howell, Robert R.

Analysis of turbojet-engine controls for afterburning starting

Description: From Introduction: "The object of this report is to investigate the effects of after-burner lighting on the engine behavior and control-system requirements of a controlled turbojet engine. In this report, a simulation procedure for the afterburner is developed (based on ref. 3), this afterburner simulation is coordinated with previously developed nonafterburning-engine simulation procedures (ref. 4), and the compensated interacting control systems of references 1 and 2 are used. The results of an analog investigation of the the effects of an afterburner light on several controlled turbojet-engine configurations are reported and evaluated."
Date: October 8, 1956
Creator: Phillips, W. E., Jr.

Analysis of Wind-Tunnel Tests at Low Speeds of a Four-Engine Propeller-Driven Airplane Configuration Having a Wing With 40 Degrees of Sweepback

Description: Report presenting an investigation to determine the effects of operating propellers on the longitudinal characteristics of a four-engine tractor airplane with a 40 degree swept wing with an aspect ratio of 10. Results regarding components of the lift changes due to operating propellers, components of the pitching-moment changes due to operating propellers, effect of configuration changes on the pitching-moment characteristics of the model, stick-fixed longitudinal stability of the model, reduction of adverse effects of propellers on longitudinal stability, and propulsive characteristics are provided.
Date: October 8, 1954
Creator: Edwards, George G. & Buell, Donald A.

Analytical and experimental investigation of the effects of compressor interstage air bleed on performance characteristics of a 13-stage axial-flow compressor

Description: Air was bled over the fifth-and tenth-stage rotor-blade rows through ports designed to pass 11 and 9 percent of the inlet flow, respectively, at 80 percent speed. Along the rated operating line the maximum speed at which rotating stall was encountered was lowered by either of these bleeds, and the stall patterns below these speeds were altered so that no dangerous resonant rotor-blade bending vibrations were excited. The combination of the two bleeds completely eliminated rotating stall to at least 50 percent speed. The compressor-discharge weight flow was decreased only at intermediate speeds, and the overall pressure ratio was affected only at intermediate speeds, and the overall pressure ratio was affected only by the combination bleed at intermediate speeds. Fifth-stage bleed increased compressor efficiency at low speeds, and tenth-stage bleed decreased efficiency at intermediate speeds.
Date: February 8, 1957
Creator: Lucas, James G.; Geye, Richard P. & Calvert, Howard F.

An analytical method for evaluating factors affecting application of transpiration cooling to gas turbine blades

Description: From Introduction: "A survey of some of the advantages and problems associated with transpiration cooling of gas-turbine engines is given in reference 1, and its is shown therein that high pressure gradients around the periphery of gas-turbine blades require that the blade wall permeability be varied around the blade periphery in order for uniform cooling to be obtained over the entire blade surface. This fact is verified in experimental investigations of transpiration-cooled turbine blades mounted in a static cascade (references 2 and 3) where it is shown that although transpiration cooling results in extremely effective cooling in the midchord region of the blade, there are very large variations in the chordwise temperature distribution because of improper permeability variation."
Date: September 8, 1952
Creator: Esgar, Jack B.

An analytical study of sideslip angles and vertical-tail loads in rolling pullouts as affected by some characteristics of modern high-speed airplane configurations

Description: From Introduction: "The rolling-pullout maneuver (any maneuver in which rolls occur during high g flight conditions) has been shown to be pertinent to design considerations from the standpoint of the loads produced on a vertical tail (refs. 1 to 3). In order to understand this problem better, the results of an analytical study of effects of large variations of some of the lateral-stability-derivative coefficients on the maximum angle of sideslip at first peak of its oscillation are presented in this paper. Also, expressions for estimating the effects of small variations of or errors in these coefficients on the maximum sideslip angle have been developed and are presented. "
Date: October 8, 1953
Creator: Stone, Ralph W., Jr.