You limited your search to:

  Partner: UNT Libraries Government Documents Department
 Decade: 1950-1959
 Year: 1955
ABSOLUTE THERMAL NEUTRON DETERMINATION. PART II. ABSOLUTE BETA COUNTING OF INDIUM FOILS

ABSOLUTE THERMAL NEUTRON DETERMINATION. PART II. ABSOLUTE BETA COUNTING OF INDIUM FOILS

Date: October 1, 1955
Creator: Koontz, R.L.; Greenfield, M.A. & Jarrett, A.A.
Description: Correction factors for the effect of thickness on the selfscattering, self-absorption, and backscattering of beta particles from indium foils were determined for irradiated foils of 0.03 to 100 mg/cm/sup 2/. The data were corrected for the activity produced by epithermal neutrons, self-shielding of thermal neutrons by the foil during irradiation, the backscatter from the foil support, and the contributions of gamma and x rays to the counting rate. The multiple beta spectra of indium produced a minimum in the self-absorption and self-scattering correction curve in the GM detector at approximately 1 mg/cm/ sup 2/ and a maximum at approximately 12 mg/cm/sup 2/. The selfabsorption curve for indium in the 2 pi counter has the expected shape for a beta emitter with multiple spectra. The self-scattering and self-absorption correction factors for a 100 mg/cm/sup 2/ indium foil are approximately 1.5 for a GM detector at 7% geometry and approximately 3 for a 2 pi counter. (D.L.C.)
Contributing Partner: UNT Libraries Government Documents Department
Acceleration characteristics of a turbojet engine with variable-position inlet guide vanes

Acceleration characteristics of a turbojet engine with variable-position inlet guide vanes

Date: July 7, 1955
Creator: Dobson, W F & Wallner, Lewis E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An accurate and rapid method for the design of supersonic nozzles

An accurate and rapid method for the design of supersonic nozzles

Date: February 1955
Creator: Beckwith, Ivan E & Moore, John A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Acoustic analysis of ram-jet buzz

Acoustic analysis of ram-jet buzz

Date: November 1955
Creator: Mirels, Harold
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Acoustic radiation from two-dimensional rectangular cutouts in aerodynamic surfaces

Acoustic radiation from two-dimensional rectangular cutouts in aerodynamic surfaces

Date: August 1955
Creator: Krishnamurty, K
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Acoustical treatment for the NACA 8- by 6-foot supersonic propulsion wind tunnel

Acoustical treatment for the NACA 8- by 6-foot supersonic propulsion wind tunnel

Date: June 1955
Creator: Beranek, Leo L; Labate, Samuel & Ingard, Uno
Description: None
Contributing Partner: UNT Libraries Government Documents Department
S-Acyl Thioctic Acid Derivatives in Aerobacter Aerogenes andScenedesmus

S-Acyl Thioctic Acid Derivatives in Aerobacter Aerogenes andScenedesmus

Date: March 30, 1955
Creator: Milhaud, Gerard; Benson, Andrew A.; Fuller, R. Clinton; Milhaud,Vera & Calvin, M.
Description: 1. Acetyl thioctic acid has been prepared chemically and i t s chromatographic and acetylating behavior i s described. 2. A C{sup 14} -containing substance has been found in Scenedesmus, photosynthesizing in the presence of a-C{sup 14}-pyruvate, which has properties suggesting that it i s acetyl thioctic acid. 3 . A C{sup 14}-containing substance has been found in Aerobacter aerogenes, metabolizing a-C{sup 14}-pyruvate, which shows the properties of a labile conjugate of thioctic acid with some relatively polar groups. 4. Acetyl thioctic acid i s formed in vitro when light acts on a solution of thioctic acid and pyruvate.
Contributing Partner: UNT Libraries Government Documents Department
Adaptation of Combustion Principles to Aircraft Propulsion, Volume I, Basic Considerations in the Combustion of Hydrocarbon Fuels with Air

Adaptation of Combustion Principles to Aircraft Propulsion, Volume I, Basic Considerations in the Combustion of Hydrocarbon Fuels with Air

Date: April 1, 1955
Creator: Barnett, Henry C. & Hibbard, Robert R.
Description: The report summarizes source material on combustion for flight-propulsion engineers. First, several chapters review fundamental processes such as fuel-air mixture preparation, gas flow and mixing, flammability and ignition, flame propagation in both homogenous and heterogenous media, flame stabilization, combustion oscillations, and smoke and carbon formation. The practical significance and the relation of these processes to theory are presented. A second series of chapters describes the observed performance and design problems of engine combustors of the principal types. An attempt is made to interpret performance in terms of the fundamental processes and theories previously reviewed. Third, the design of high-speed combustion systems is discussed. Combustor design principles that can be established from basic considerations and from experience with actual combustors are described. Finally, future requirements for aircraft engine combustion systems are examined.
Contributing Partner: UNT Libraries Government Documents Department
Additional comparisons between computed and measured transonic drag-rise coefficients at zero lift for wing-body-tail configurations

Additional comparisons between computed and measured transonic drag-rise coefficients at zero lift for wing-body-tail configurations

Date: August 15, 1955
Creator: Holdaway, George H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Additional experimental heat-transfer and durability data on several forced-convection, air-cooled, strut-supported turbine blades of improved design

Additional experimental heat-transfer and durability data on several forced-convection, air-cooled, strut-supported turbine blades of improved design

Date: January 19, 1955
Creator: Schum, Eugene F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Additional measurements of the low-speed static stability of a configuration employing three triangular wing panels and a body of equal length

Additional measurements of the low-speed static stability of a configuration employing three triangular wing panels and a body of equal length

Date: July 25, 1955
Creator: Delany, Noel K
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An advisory committee report on local government

An advisory committee report on local government

Date: June 1955
Creator: United States. Commission on Intergovernmental Relations. Advisory Committee on Local Government.
Description: The ACIR Library is composed of publications that study the interactions between different levels of government. This document addresses local government.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic and hydrodynamic characteristics of models of some aircraft-towed mine-sweeping devices : TED No. NACA AR 8201

Aerodynamic and hydrodynamic characteristics of models of some aircraft-towed mine-sweeping devices : TED No. NACA AR 8201

Date: December 1, 1955
Creator: Shanks, Robert E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics and pressure distributions of a 6-percent-thick 49 degree sweptback wing with blowing over half-span and full-span flaps

Aerodynamic characteristics and pressure distributions of a 6-percent-thick 49 degree sweptback wing with blowing over half-span and full-span flaps

Date: September 20, 1955
Creator: Whittle, Edward F , Jr & Mclemore, H Clyde
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at Mach numbers from 0.7 to 1.75 of a four-engine swept-wing airplane configuration as obtained from a rocket-propelled model test

Aerodynamic characteristics at Mach numbers from 0.7 to 1.75 of a four-engine swept-wing airplane configuration as obtained from a rocket-propelled model test

Date: September 2, 1955
Creator: Chapman, Rowe, Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a 0.04956-scale model of the Convair F-102A airplane at Mach numbers of 1.41, 1.61, and 2.01

Aerodynamic characteristics of a 0.04956-scale model of the Convair F-102A airplane at Mach numbers of 1.41, 1.61, and 2.01

Date: September 30, 1955
Creator: Spearman, M. Leroy & Driver, Cornelius
Description: Tests have been made in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.41, 1.61, and 2.01 of various arrangements of a 0.04956-scale model of the Convair F-102A airplane with faired inlets. Tests made of the model equipped with a plain wing, a wing with 6.4 percent conical camber, and a wing with 15 percent conical camber. Body modifications including an extended nose, a modified canopy, and extended afterbody fillets were evaluated. In addition, the effects of a revised vertical tail and two different ventral fins were determined. The results indicated that the use of cambered wings resulted in lower drag in the lift-coefficient range above 0.2. This range, however, is above that which would generally be required for level flight; hence, the usefulness of camber might be confined to increased maneuverability at the higher lifts while its use may be detrimental to the high-speed (low-lift) capabilities.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic Characteristics of a 0.04956-Scale Model of the Convair F-102A Airplane at Transonic Speeds

Aerodynamic Characteristics of a 0.04956-Scale Model of the Convair F-102A Airplane at Transonic Speeds

Date: March 28, 1955
Creator: Tempelmeyer, Kenneth E. & Osborne, Robert S.
Description: Tests have been conducted in the Langley 8-foot transonic tunnel on a 0.04956-scale model of the Convair F-102A airplane which employed an indented and extended fuselage, cambered wing leading edges, and deflected wing tips. Force and moment characteristics were obtained for Mach numbers from 0.60 to 1.135 at angles of attack up to 20 . In addition, tests were made over a limited angle-of-attack range to determine the effects of the cambered leading edges, deflected tips, and a nose section with a smooth area distribution. Fuselage modifications employed on the F-102A were responsible for a 25.percent reduction in the minimum drag-coefficient rise between the Mach numbers of 0.85 and 1.075 when compared with that for the earlier versions of the F-102. Although the wing modifications increased the F-102A subsonic minimum drag-coefficient level approximately 0.0020, they produced large decreases in drag at lifting conditions over that for the original (plane-wing) F-102. The F-102A had 15 to 25 percent higher maximum lift-drag ratios than did the original F-102. The F-102A had about 15 percent lower maximum lift-drag ratios at Mach numbers below 0.95 and slightly higher maximum lift-drag ratios at supersonic speeds when compared with those ratios for sn earlier modified-wing version ...
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a 1/4-scale model of the duct system for the General Electric P-1 nuclear powerplant for aircraft

Aerodynamic characteristics of a 1/4-scale model of the duct system for the General Electric P-1 nuclear powerplant for aircraft

Date: July 29, 1955
Creator: Wood, Charles C. & Henry, John R.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a 60 degree delta wing having a half-delta tip control at a Mach number of 4.04

Aerodynamic characteristics of a 60 degree delta wing having a half-delta tip control at a Mach number of 4.04

Date: April 25, 1955
Creator: Ulmann, Edward F & Smith, Fred M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a small-scale shrouded propeller at angles of attack from 0 to 90 degrees

Aerodynamic characteristics of a small-scale shrouded propeller at angles of attack from 0 to 90 degrees

Date: November 1, 1955
Creator: Parlett, Lysle P
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of NACA 0012 airfoil section at angles of attack from 0 degrees to 180 degrees

Aerodynamic characteristics of NACA 0012 airfoil section at angles of attack from 0 degrees to 180 degrees

Date: January 1, 1955
Creator: Critzos, Chris C; Heyson, Harry H & Boswinkle, Robert W , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of several 6-percent-thick airfoils at angles of attack from 0 degrees to 20 degrees at high subsonic speeds

Aerodynamic characteristics of several 6-percent-thick airfoils at angles of attack from 0 degrees to 20 degrees at high subsonic speeds

Date: May 1, 1955
Creator: Daley, Bernard N & Lord, Douglas R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of two rectangular-plan-form, all moveable controls in combination with a slender body of revolution at Mach numbers from 3.00 to 6.25

Aerodynamic characteristics of two rectangular-plan-form, all moveable controls in combination with a slender body of revolution at Mach numbers from 3.00 to 6.25

Date: December 28, 1955
Creator: Wong, Thomas J & Gloria, Hermilo R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic Characteristics of Two Rectangular-plan-form, Allmovable Controls in Combination With a Slender Body of Revolution at Mach Numbers From 3.00 to 6.25

Aerodynamic Characteristics of Two Rectangular-plan-form, Allmovable Controls in Combination With a Slender Body of Revolution at Mach Numbers From 3.00 to 6.25

Date: December 28, 1955
Creator: Gloria, H. R. & Wong, T. J.
Description: Aerodynamic characteristics of rectangular planform, all-movable controls combined with slender body of revolution at mach 3 to 6.25.
Contributing Partner: UNT Libraries Government Documents Department
FIRST PREV 1 2 3 4 5 NEXT LAST