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  Partner: UNT Libraries Government Documents Department
 Resource Type: Report
 Decade: 1950-1959
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: January 1, 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 1, 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: None
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
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