UNT Libraries Government Documents Department - 27 Matching Results

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Zirconium analysis

Description: Recent attempts to displace fixed plutonium from the body by zirconium therapy have made an analytical method for the determination of zirconium in urine salts advisable. Standard chemical analytical methods for zirconium in rock were not adaptable to urine salts. The poor results obtained from these standard methods necessitated the development of a modified analytical procedure. The results of this work are reported herein.
Date: February 21, 1950
Creator: Thorburn, R. C.
Item Type: Refine your search to only Report
open access

Terminal Report on the Radiolanthanum Laboratory

Description: "The purpose of this present document is twofold: (1) To acquaint the reader with the planning of the radiochemical laboratory designed for the analytical control of the Radio-lanthanum Process. (2) To define the terminal status of the design of this laboratory and its equipment."
Date: July 21, 1950
Creator: Figenshau, J. K.
Item Type: Refine your search to only Report
open access

Corrosion of Redox Waste Storage Tank Construction Materials

Description: From introduction:"It was the aim of this investigation to determine the resistance of several materials of construction to current and anticipated and anticipated Hanford separation process waste streams under specific conditions. The corrosion rates of mild steel and austenitic stainless steel and the resistance of several commercial protective coatings were established."
Date: August 21, 1950
Creator: Koenig, W. W. & Sanborn, K. L.
Item Type: Refine your search to only Report
open access

Wind-tunnel tests of a 0.16-scale model of the X-3 airplane at high subsonic speeds: stability and control characteristics

Description: Report presenting static lateral- and longitudinal-stability tests of a scale model of a projected, low-aspect-ratio, supersonic airplane at low and high subsonic Mach numbers. The wing was equipped with leading-edge flaps and had a modified double-wedge airfoil with sharp leading and trailing edges. Results regarding lift characteristics, static longitudinal stability and control, lateral and directional stability, drag characteristics, and wing and fuselage tuft studies are provided.
Date: April 21, 1950
Creator: Hamilton, William T. & Cleary, Joseph W.
Item Type: Refine your search to only Report
open access

The Effect of the Inlet Mach Number and Inlet-Boundary-Layer Thickness on the Performance of a 23 Degree Conical-Diffuser-Tail-Pipe Combination

Description: An investigation was conducted to determine the effect of the inlet Mach number and entrance-boundary-layer thickness on the performance of a 23 degree 21-inch conical-diffuser - tail-pipe combination with a 2:1 area ratio. The air flows used in this investigation covered an inlet Mach number range from 0.17 to 0.89 and corresponding Reynolds numbers of 1,700,000 to 7,070,000. Results are reported for two inlet-boundary-layer thicknesses.
Date: March 21, 1950
Creator: Persh, Jerome
Item Type: Refine your search to only Report
open access

Free-Flight Investigation of the Static and Dynamic Longitudinal Stability Characteristics of 1/3.7-Scale Rocket-Powered Models of the Bell MX-776A

Description: "An investigation of the static and dynamic longitudinal stability characteristics of 1/3.7 scale rocket-powered model of the Bell MX-776A has been made for a Mach number range from 0.8 to 1.6. Two models were tested with all control surfaces at 0 degree deflection and centers of gravity located 1/4 and 1/2 body diameters, respectively, ahead of the equivalent design location. Both models were stable about the trim conditions but did not trim at 0 degree angle of attack because of slight constr… more
Date: February 21, 1950
Creator: Michal, David H.
Item Type: Refine your search to only Report
open access

Preliminary correlation of efficiency of aircraft gas-turbine combustors for different operating conditions

Description: Report presenting a correlation of combustion-efficiency data obtained in experimental investigations with 14 aircraft gas-turbine combustors. The precision is not good for some combustors, but can help in predicting the efficiency at different operating conditions and in comparing the performance of different combustors from data obtained in unrelated tests.
Date: September 21, 1950
Creator: Childs, J. Howard
Item Type: Refine your search to only Report
open access

Internal film cooling experiments in 4-inch duct with gas temperatures to 2000 degrees F

Description: Report presenting an investigation of the cooling effectiveness of water films on the inner surface of a well-insulated, 4-inch-diameter duct with air flowing through the duct at a range of temperature and Reynolds numbers. Results regarding the effect of the gas temperature and mass velocity on liquid-cooled length, effect of coolant flow on liquid-cooled length, and some suggestions for further investigation are provided. Equations for correlation are created from the data.
Date: September 21, 1950
Creator: Kinney, George R. & Sloop, John L.
Item Type: Refine your search to only Report
open access

Some Effects of Chordwise Fences on the Aerodynamic Characteristics of Four Moderately Sweptback Wings in the Low-Lift Range at Transonic Mach Numbers and at Mach Number 1.9

Description: Report presenting a study of data from wind-tunnel investigations to determine the effects of thin chordwise fences on some of the aerodynamic characteristics of four moderately sweptback wings at a low-lift range. The fences caused no large detrimental effects on lift or pitching moment at transonic or supersonic speeds. Results regarding the increment of drag coefficient due to fences, effect of fences on the lift coefficient and longitudinal stability, and effects on aileron effectiveness ar… more
Date: July 21, 1950
Creator: Guy, Lawrence D.
Item Type: Refine your search to only Report
open access

Aerodynamic characteristics of NACA RM-10 missile in 8- by 6-foot supersonic wind tunnel at Mach numbers from 1.49 to 1.98 2: presentation and analysis of force measurements

Description: Experimental investigation of aerodynamic forces acting on body of revolution (NACA RM-10 missile) with and without stabilizing fins was conducted at Mach numbers from 1.49 to 1.98 at angles of attack from 0 to 9 degrees and at Reynolds number of approximately 30,000,000. Comparison of experimental lift, drag, and pitching-moment coefficients and center of pressure location for body alone is made with linearized potential theory and a semiempirical method. Results indicate that aerodynamic char… more
Date: July 21, 1950
Creator: Esenwein, Fred T.; Obery, Leonard J. & Schueller, Carl F.
Item Type: Refine your search to only Report
open access

Cooling of ram jets and tail-pipe burners: analytical method for determining temperatures of combustion chamber having annular cooling passage

Description: Report presenting an analytical method for calculating the maximum wall temperature of a tail-pipe burner or a ramjet combustion chamber cooled by air or gas flowing through a surrounding annular passage.
Date: March 21, 1950
Creator: Koffel, William K.; Stamper, Eugene & Sanders, Newell D.
Item Type: Refine your search to only Report
open access

Altitude-Wind-Tunnel Investigation of Turbine Performance in J47 Turbojet Engine

Description: From Introduction: "Performance data are presented in this report to show the characteristics of the turbine operating as an integral part of the engine. Typical results are graphically presented to show the effects of changes in altitude, flight Mach number, and exhaust-nozzle-outlet area on turbine performance. All turbine-performance data obtained are given in tabular form."
Date: September 21, 1950
Creator: Thorman, H. Carl & McAulay, John E.
Item Type: Refine your search to only Report
open access

Effect of an End Plate on the Aerodynamic Characteristics of a 20.55 Degree Sweptback Wing with an Aspect Ratio of 2.67 and a Taper Ratio of 0.5.: Transonic-Bump Method

Description: "An investigation by the transonic-bump method conducted in the Langley high-speed 7- by 10-foot tunnel to determine the effect of an end plate on the aerodynamic characteristics of a 20.55 degree sweptback wing with an aspect ratio of 2.67 and a taper ratio of 0.5 indicated that the end plate affected the aerodynamic characteristics of the wing at transonic Mach numbers in the same manner as has been observed for swept and unswept wings at low speeds" (p. 1).
Date: December 21, 1950
Creator: Watson, James M.
Item Type: Refine your search to only Report
open access

Wind-Tunnel Investigation at Low Speed of a Wing Swept Back 63 Degrees and Twisted and Cambered for Uniform Load at a Lift Coefficient of 0.5 and With a Thickened Tip Section

Description: Report discusses the result of tests determining the longitudinal-stability characteristics and spanwise distribution of load of a wing model with the leading edge swept back 63 degrees, a thickened tip section, and a twisted and cambered shape. The wing was tested with a fuselage and various devices for altering stall and spanwise boundary-layer flow. Measurements of force, pressure-distribution, and span load distribution are described.
Date: November 21, 1950
Creator: Weiberg, James A. & Carel, Hubert C.
Item Type: Refine your search to only Report
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