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  Partner: UNT Libraries Government Documents Department
 Decade: 1950-1959
 Year: 1950
4-Channel Line Driver: Modified

4-Channel Line Driver: Modified

Date: 1950?
Creator: Titterton, E. W.
Description: Technical drawing of line drivers and amplifiers for use in nuclear reactors.
Contributing Partner: UNT Libraries Government Documents Department
An 8-foot axisymmetrical fixed nozzle for subsonic Mach numbers up to 0.99 and for a supersonic Mach number of 1.2

An 8-foot axisymmetrical fixed nozzle for subsonic Mach numbers up to 0.99 and for a supersonic Mach number of 1.2

Date: February 23, 1950
Creator: Ritchie, Virgil S; Wright, Ray H & Tulin, Marshall P
Description: None
Contributing Partner: UNT Libraries Government Documents Department
30 Rv. Power Supply

30 Rv. Power Supply

Date: 1950?
Creator: U.S. Atomic Energy Commission
Description: Technical drawing of electronic circuits and power supplies to nuclear reactors.
Contributing Partner: UNT Libraries Government Documents Department
234-5 Development Group - summary report, use of {open_quotes}AT{close_quotes} solution without evaporation

234-5 Development Group - summary report, use of {open_quotes}AT{close_quotes} solution without evaporation

Date: September 1, 1950
Creator: Lyon, W.L. & Facer, J.F.
Description: A summary of work is presented from the 234-5 Development Group, September 1, 1950, with regard to the feasibility of transferring the plutonium processing solution, without evaporation, to the Purification Building. Critical factors identified were the concentration of the nitric acid and temperature.
Contributing Partner: UNT Libraries Government Documents Department
234-5 Development summary report: Recovery of plutonium from skulls

234-5 Development summary report: Recovery of plutonium from skulls

Date: October 12, 1950
Creator: Lyon, W.L. & Facer, J.F.
Description: Short communication.
Contributing Partner: UNT Libraries Government Documents Department
THE 1A HYBRID FLOWSHEET

THE 1A HYBRID FLOWSHEET

Date: January 1, 1950
Creator: Coplan, B.V.; Davidson, J.K.; Hass, W.O. & Zebroski, E.L.
Description: A preliminary hybrid 1A flowsheet in which the extraction section operates substantially acid while the scrub section is acid deficient is presented. The effects of added nitric acid on the performance of the acid deficient 1A flowsheet are considered, and the need for control of the entering stream acidities in such flowsheets is evaluated. Data on batch-countercurrent decontamination and plutonium recovery are included. (J.R.D.)
Contributing Partner: UNT Libraries Government Documents Department
Ability of pilots to control simulated short-period yawing oscillations

Ability of pilots to control simulated short-period yawing oscillations

Date: November 13, 1950
Creator: Phillips, William H & Cheatham, Donald C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The absorption, distribution, and excretion of tritium in men and animals

The absorption, distribution, and excretion of tritium in men and animals

Date: November 24, 1950
Creator: Pinson, E.A. & Anderson, E.C.
Description: A series of experiments on exposure of man and rats to tritium gas (HT) or tritiated water (HTO) are reported. In one human experiment 3 millicuries of HTO was administered in 200 milliliters of water by ingestion. Absorption into the blood stream was linear with time and complete in about 45 minutes. Body water turnover was measured over a period of six days by weighing all food and fluid intake and all excretory output. For four days water turnover was kept near normal (2.7 liters per day). During the last two days water turnover was increased to 12.8 liters per day. Tritium excretion rates was determined on eight other human subjects in which water turnover in which measured less precisely. The biological half-life of HTO in nine human subjects varied from 9 to 14 days on ad libitum and was reduced to 2 1/2 days in one subject on high water intake. The tritium activity in sweat, expired water vapor, septum and urine was found to be essentially the same as that in water from the blood. Rats were continually exposed to various concentrations of tritium in inspired air (0.000001 to 0.03 microcuries per ml) for periods up to 145 ...
Contributing Partner: UNT Libraries Government Documents Department
The acute radiation syndrome: A study of ten cases and a review of the problem

The acute radiation syndrome: A study of ten cases and a review of the problem

Date: March 17, 1950
Creator: Hempelmann, L.H. & Lisco, H.
Description: In this report ten cases of acute radiation syndrome are described resulting from two accidents occurring at the Los Alamos Scientific Laboratory of unique nature involving fissionable material. These cases are described in considerable detail. The report comprises ten sections. This volume, part II of the report, is comprised of sections entitled: (1) the Biological Basis for the Clinical Response seen in the Acute radiation Syndrome, (2) Clinical Signs and Symptoms, (3) Discussion of Hematological Findings, (4) Chemistry of the Blood and Urine, (5) Discussion of Pathological Findings, and (6) Reconsiderations of the Calculated Radiation Doses in Terms of the Observed Biological Response of the Patients. This report was prepared primarily for the clinician who is interested in radiation injuries and therefore emphasis has been placed on the correlation of clinical and pathological changes with the type of cytogenetic change known to be produced by ionizing radiation.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic and lateral-control characteristics of a 1/28-scale model of the Bell X-1 airplane wing-fuselage combination : transonic-bump method

Aerodynamic and lateral-control characteristics of a 1/28-scale model of the Bell X-1 airplane wing-fuselage combination : transonic-bump method

Date: May 5, 1950
Creator: Lockwood, Vernard E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at a Mach number of 1.25 of a 6-percent-thick triangular wing and 6- and 9-percent-thick triangular wings in combination with a fuselage : wing aspect ratio 2.31, biconvex airfoil sections

Aerodynamic characteristics at a Mach number of 1.25 of a 6-percent-thick triangular wing and 6- and 9-percent-thick triangular wings in combination with a fuselage : wing aspect ratio 2.31, biconvex airfoil sections

Date: May 5, 1950
Creator: Hall, Albert W & Morris, Garland J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at a Mach number of 1.38 of four wings of aspect ratio 4 having quarter-chord sweep angles of 0 degrees, 35 degrees, 45 degrees, and 60 degrees

Aerodynamic characteristics at a Mach number of 1.38 of four wings of aspect ratio 4 having quarter-chord sweep angles of 0 degrees, 35 degrees, 45 degrees, and 60 degrees

Date: October 10, 1950
Creator: Kemp, William B , Jr; Goodson, Kenneth W & Booth, Robert A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at Reynolds numbers of 3.0 x 10(exp 6) and 6.0 x 10(exp 6) of three airfoil sections formed by cutting off various amounts from the rear portion of the NACA 0012 airfoil section

Aerodynamic characteristics at Reynolds numbers of 3.0 x 10(exp 6) and 6.0 x 10(exp 6) of three airfoil sections formed by cutting off various amounts from the rear portion of the NACA 0012 airfoil section

Date: April 1, 1950
Creator: Smith, Hamilton A & Schaefer, Raymond F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a wing with quarter-chord line swept back 45 degrees, aspect ratio 6, taper ratio 0.6, and NACA 65A009 airfoil section

Aerodynamic characteristics of a wing with quarter-chord line swept back 45 degrees, aspect ratio 6, taper ratio 0.6, and NACA 65A009 airfoil section

Date: April 6, 1950
Creator: Spreemann, Kenneth P; Morrison, William D , Jr & Pasteur, Thomas B , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a wing with quarter-chord line swept back 60 degrees, aspect ratio 2, taper ratio 0.6, and NACA 65A006 airfoil section : transonic bump method

Aerodynamic characteristics of a wing with quarter-chord line swept back 60 degrees, aspect ratio 2, taper ratio 0.6, and NACA 65A006 airfoil section : transonic bump method

Date: February 24, 1950
Creator: Myers, Boyd C , II & King, Thomas J , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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

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

Date: March 8, 1950
Creator: Polhamus, Edward C & Campbell, George S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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

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

Date: May 8, 1950
Creator: Myers, Boyd C , II & Wiggins, James W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of damping screens

Aerodynamic characteristics of damping screens

Date: January 1, 1950
Creator: Schubauer, G B; Spangenberg, W G & Klebanoff, P S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of NACA RM-10 missile in 8- by 6-foot supersonic wind tunnel at Mach numbers from 1.49 to 1.98 I : presentation and analysis of pressure measurements (stabilizing fins removed)

Aerodynamic characteristics of NACA RM-10 missile in 8- by 6-foot supersonic wind tunnel at Mach numbers from 1.49 to 1.98 I : presentation and analysis of pressure measurements (stabilizing fins removed)

Date: July 20, 1950
Creator: Luidens, Roger W & Simon, Paul C
Description: Experimental investigation of flow about a slender body of revolution (NACA RM-10 missile) aligned and inclined to a supersonic stream was conducted at Mach numbers from 1.49 to 1.98 at a Reynolds number of approximately 30,000,000. Boundary-layer measurements at zero angle of attack are correlated with subsonic formulations for predicting boundary-layer thickness and profile. Comparison of pressure coefficients predicted by theory with experimental values showed close agreement at zero angle of attack and angle of attack except over the aft leeward side of body. At angle of attack, pitot pressure measurements in plane of model base indicated a pair of symmetrically disposed vortices on leeward side of body.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of NACA RM-10 missile in 8- by 6-foot supersonic wind tunnel at Mach numbers from 1.49 to 1.98 II : presentation and analysis of force measurements

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

Date: July 21, 1950
Creator: Esenwein, Fred T; Obery, Leonard J & Schueller, Carl F
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 characteristics were predicted more accurately by semiempirical method than by potential theory. Breakdown of measured drag coefficients into components of friction, pressure, and base-pressure drag is presented for body alone at zero angle of attack.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of NACA RM 10 missile in 8 by 6 foot supersonic wind tunnel at Mach numbers from 1.49 to 1.98. III : analysis of force distribution at angle of attack (stabilizing fins removed)

Aerodynamic characteristics of NACA RM 10 missile in 8 by 6 foot supersonic wind tunnel at Mach numbers from 1.49 to 1.98. III : analysis of force distribution at angle of attack (stabilizing fins removed)

Date: December 12, 1950
Creator: Luidens, Roger W & Simon, Paul C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics with fixed and free transition of a modified delta wing in combination with fuselage at high subsonic speeds

Aerodynamic characteristics with fixed and free transition of a modified delta wing in combination with fuselage at high subsonic speeds

Date: May 2, 1950
Creator: Polhamus, Edward C & King, Thomas J , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic coefficients for an oscillating airfoil with hinged flap, with tables for a Mach number of 0.7

Aerodynamic coefficients for an oscillating airfoil with hinged flap, with tables for a Mach number of 0.7

Date: October 1, 1950
Creator: Turner, M J & Rabinowitz, S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic forces and moments on a 1/10-scale model of a fighter airplane in spinning attitudes as measured on a rotary balance in the Langley 20-foot free-spinning tunnel

The aerodynamic forces and moments on a 1/10-scale model of a fighter airplane in spinning attitudes as measured on a rotary balance in the Langley 20-foot free-spinning tunnel

Date: September 1, 1950
Creator: Stone, Ralph W , Jr; Burk, Sanger M , Jr & Bihrle, William, Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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