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  Partner: UNT Libraries Government Documents Department
 Decade: 1950-1959
 Collection: Technical Report Archive and Image Library
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 experiments with flat-top wing- body combinations at high supersonic speeds

Additional experiments with flat-top wing- body combinations at high supersonic speeds

Date: February 19, 1957
Creator: Gloria, H. R.; Syvertson, C. A. & Wong, T. J.
Description: Flat top wing body configuration effects on aerodynamic characteristics of supersonic aircraft.
Contributing Partner: UNT Libraries Government Documents Department
Additional fatigue tests on effects of design details in 355-T6 sand-cast aluminum alloy

Additional fatigue tests on effects of design details in 355-T6 sand-cast aluminum alloy

Date: March 10, 1954
Creator: Eaton, I D & Youra, John A
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
Additional results of an investigation at transonic speeds to determine the effects of a heated propulsive jet on the drag characteristics of a series of related afterbodies

Additional results of an investigation at transonic speeds to determine the effects of a heated propulsive jet on the drag characteristics of a series of related afterbodies

Date: September 24, 1956
Creator: Henry, Beverly Z JR & Cahn, Maurice S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Additional Results on the Static Longitudinal and Lateral Stability Characteristics of a 0.05-Scale Model of the Convair F2Y-1 Airplane at High Subsonic Speeds

Additional Results on the Static Longitudinal and Lateral Stability Characteristics of a 0.05-Scale Model of the Convair F2Y-1 Airplane at High Subsonic Speeds

Date: August 10, 1954
Creator: Spreeman, Kenneth P. & Few, Albert G.
Description: Additional results on the static longitudinal and lateral stability characteristics of a 0.05-scale model of the Convair F2Y-1 water-based fighter airplane were obtained in the Langley high-speed 7- by 10-foot tunnel over a Mach number range of 0.50 to 0.92. The maximum angle-of-attack range (obtained at the lower Mach numbers) was from -2 degrees to 25 degrees. The sideslip-angle range investigated was from -4 degrees to 12 degrees. The investigation included effects of various arrangements of wing fences, leading-edge chord-extensions, and leading-edge notches. Various fuselage fences, spoilers, and a dive brake also were investigated. From overall considerations of lift, drag, and pitching moments, it appears that there were two modifications somewhat superior to any of the others investigated: One was a configuration that employed a full-chord fence and a partial-chord fence located at 0.63 semispan and 0.55 semispan, respectively. The second was a leading-edge chord-extension that extended from 0.68 semispan to 0.85 semispan in combination with a leading-edge notch located at 0.68 semispan. With plus or minus 10 degrees aileron, the estimated wing-tip helix angle was reduced from 0.125 at a Mach number of 0.50 to 0.088 at a Mach number of 0.92, with corresponding rates of roll of 4.0 ...
Contributing Partner: UNT Libraries Government Documents Department
Additional static and fatigue tests of high-strength aluminum-alloy bolted joints

Additional static and fatigue tests of high-strength aluminum-alloy bolted joints

Date: July 1954
Creator: Hartmann, E C; Holt, Marshall & Eaton, I D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Additional Studies of the Stability and Controllability of an Unswept-Wing Vertically Rising Airplane Model in Hovering Flight Including Studies of Various Tethered Landing Techniques

Additional Studies of the Stability and Controllability of an Unswept-Wing Vertically Rising Airplane Model in Hovering Flight Including Studies of Various Tethered Landing Techniques

Date: November 6, 1951
Creator: Bates, William R.; Lovell, Powell M., Jr. & Smith, Charles C., Jr.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The adhesion of molten boron oxide to various materials

The adhesion of molten boron oxide to various materials

Date: April 1, 1958
Creator: Witzke, W R
Description: From Introduction: "The present report evaluates the amount of adhesion existing between the liquid boron oxide and various materials used in engines."
Contributing Partner: UNT Libraries Government Documents Department
Adhesive and protective characteristics of ceramic coating A-417 and its effect on engine life of forged Refractaloy-26 (AMS 5760) and cast stellite 21 (AMS 5385) turbine blades

Adhesive and protective characteristics of ceramic coating A-417 and its effect on engine life of forged Refractaloy-26 (AMS 5760) and cast stellite 21 (AMS 5385) turbine blades

Date: February 12, 1953
Creator: Garrett, Floyd B & Gyorgak, Charles A
Description: The adhesive and protective characteristics of National Bureau of Standards Coating A-417 were investigated, as well as the effect of the coating on the life of forged Refractaloy 26 and cast Stellite 21 turbine blades. Coated and uncoated blades were run in a full-scale J33-9 engine and were subjected to simulated service operations consisting of consecutive 20-minute cycles (15 min at rated speed and approximately 5 min at idle). The ceramic coating adhered well to Refractaloy 26 and Stellite 21 turbine blades operated at 1500 degrees F. The coating also prevented corrosion of the Refractaloy 26, a corrosion-sensitive nickel-base alloy, and of the Stellite 21, a relatively corrosion-resistant cobalt-base alloy. Although the coating prevented corrosion of both alloys, it had no apparent effect on blade life.
Contributing Partner: UNT Libraries Government Documents Department
Advanced Designs of Magnetic Jack-Type Control Rod Drive

Advanced Designs of Magnetic Jack-Type Control Rod Drive

Date: November 1959
Creator: Young, Joseph N.
Description: Report containing information regarding magnetic jacks, which are devices used "for positioning the control rods in a nuclear reactor, especially in a reactor containing water under pressure" (page 9). Contains a description of the device, its use, test results, and illustrations.
Contributing Partner: UNT Libraries Government Documents Department
Advanced Pressurized Water Reactor Study [Part 3]: 235 Mw Coal-fired Generating Plant

Advanced Pressurized Water Reactor Study [Part 3]: 235 Mw Coal-fired Generating Plant

Date: July 1959
Creator: U.S. Atomic Energy Commission. Division of Reactor Development.
Description: ...
Contributing Partner: UNT Libraries Government Documents Department
AEC Hot Cells and Related Facilities

AEC Hot Cells and Related Facilities

Date: May 1958
Creator: Fosdick, Ellery R.
Description: Foreward: The primary purpose of this report is to present as an accumulation of basic information on the hot cells constructed to date by the United States Atomic Energy Commission.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic and hydrodynamic characteristics of a deck-inlet multijet water-based-aircraft configuration designed for supersonic flight

Aerodynamic and hydrodynamic characteristics of a deck-inlet multijet water-based-aircraft configuration designed for supersonic flight

Date: December 5, 1956
Creator: Bielat, Ralph P; Coffee, Claude W , Jr & Petynia, William W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic and hydrodynamic characteristics of a proposed supersonic multijet water-based hydro-ski aircraft with a variable-incidence wing

Aerodynamic and hydrodynamic characteristics of a proposed supersonic multijet water-based hydro-ski aircraft with a variable-incidence wing

Date: October 23, 1957
Creator: Petynia, William W; Hasson, Dennis F & Spooner, Stanley H
Description: None
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 and inlet-flow-field characteristics at a free-stream Mach number of 3.0 for airplanes with circular fuselage cross sections and for two engine locations

Aerodynamic and inlet-flow-field characteristics at a free-stream Mach number of 3.0 for airplanes with circular fuselage cross sections and for two engine locations

Date: March 18, 1958
Creator: Dryer, Murray & Luidens, Roger W
Description: None
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
The aerodynamic behavior of a harmonically oscillating finite sweptback wing in supersonic flow

The aerodynamic behavior of a harmonically oscillating finite sweptback wing in supersonic flow

Date: October 1951
Creator: Chang, Chieh-Chien
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics and flying qualities of a tailless triangular-wing airplane configuration as obtained from flights of rocket-propelled models at transonic and supersonic speeds

Aerodynamic characteristics and flying qualities of a tailless triangular-wing airplane configuration as obtained from flights of rocket-propelled models at transonic and supersonic speeds

Date: November 1956
Creator: Mitcham, Grady L; Stevens, Joseph E & Norris, Harry P
Description: A flight investigation of rocket-powered models of a tailless triangular-wing airplane configuration was made through the transonic and low supersonic speed range at the Langley Pilotless Aircraft Research Station at Wallops Island, Va. An analysis of the aerodynamic coefficients, stability derivatives, and flying qualities based on the results obtained from the successful flight tests of three models is presented.
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 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 a Mach Number of 6.8 of Two Hypersonic Missile Configurations, One with Low-Aspect-Ratio Cruciform Fins and Trailing-Edge Flaps and One with a Flared Afterbody and All-Movable Controls

Aerodynamic Characteristics at a Mach Number of 6.8 of Two Hypersonic Missile Configurations, One with Low-Aspect-Ratio Cruciform Fins and Trailing-Edge Flaps and One with a Flared Afterbody and All-Movable Controls

Date: August 4, 1958
Creator: Bernot, P. T. & Robinson, R. B.
Description: None
Contributing Partner: UNT Libraries Government Documents Department