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An Introduction to the Description and Evaluation of Microwave Systems Using Terminal Invariant Parameters

Description: Report presenting the technical background and basis for a new method of evaluating certain performance parameters which are common to all microwave systems. A unique feature of the new measurement concept is its elimination of the precision waveguide and connector requirements for an important class of measurement problems.
Date: October 1969
Creator: Engen, Glenn F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Introduction to the Helicopter

Description: It is the object of this report to review briefly the aerodynamic and construction data already available regarding helicopters and to set forth the difficulties which must be met.
Date: 1925
Creator: Klemin, Alexander
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An introduction to the physical aspects of helicopter stability

Description: "In order to provide engineers interested in rotating-wing aircraft but with no specialized training in stability theory some understanding of the factors that influence the flying qualities of the helicopter, an explanation is made of both the static stability and the stick-fixed oscillation in hovering and forward flight in terms of fundamental physical qualities. Three significant stability factors - static stability with angle of attack, static stability with speed, and damping due to a pit… more
Date: November 1949
Creator: Gessow, Alfred & Amer, Kenneth B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An introduction to the physical aspects of helicopter stability

Description: In order to provide engineers interested in rotating-wing aircraft, but with no specialized training in stability theory, some understanding of the factors that influence the flying qualities of the helicopter, an explanation is made of both the static stability and the stick-fixed oscillation in hovering and forward flight in terms of fundamental physical quantities. Three significant stability factors -- static stability with angle of attack, static stability with speed, and damping due to a … more
Date: September 19, 1949
Creator: Gessow, Alfred & Amer, Kenneth B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Introduction to the Problem of Rocket-Powered Aircraft Performance

Description: An introduction to the problem of determining the fundamental limitations on the performance possibilities of rocket-powered aircraft is presented. Previous material on the subject is reviewed and given in condensed form along with supplementary analyses. Some of the problems discussed are: 1) limiting velocity of a rocket projectile; 2) limiting velocity of a rocket jet; 3) jet efficiency; 4) nozzle characteristics; 5) maximum attainable altitudes; 6) ranges. Formulas are presented relating th… more
Date: December 1947
Creator: Ivey, H. Reese; Bowen, Edward N., Jr. & Oborny, Lester F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Inundated Anthracite Reserves: Eastern Middle Field of Pennsylvania

Description: From Scope of Report: "In this report one major unwatering project was developed. Three pools that inundate considerable tonnages of anthracite reserves are close enough together to be unwatered by some centralized system. Three alternative plans were studied to estimate the cost of each."
Date: 1950
Creator: Ash, S. H. (Simon Harry), b. 1889; Kynor, H. D.; Fatzinger, R. W.; Davies, B. S. & Gilbert, J. C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Invariant Solutions of the Exact Bethe-Saltpeter Equation in General-Mass Case

Description: The invariant solutions of the Bethe-Saltpeter equation in an approximation which is more general than the ladder approximation are found in the case of non-zero exchanged-meson mass. They are expressed as series of "truncated vertex functions," which are certain combinations of the usual vertex functions. The eigenvalues of the coupling constant are determined by a transcendental equation, which is not solved explicitly.
Date: 1962
Creator: Nakanishi, Noboru
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Invention Report: Hermetically Sealed Closure on a Sheathed Thermocouple

Description: Applications of sheathed (metal) thermocouples may require in many instances, the insertion of the thermocouple thermal junction into an area that must be hermetically sealed to the outside. This same area usually contains highly reactive heat transfer medium such as an eutectic alloy of sodium and potassium of sodium alone. When fissionable materials are being irradiated, fission products that are driven off would also be present and must be contained under varying temperatures and pressures.
Date: July 12, 1960
Creator: Kosut, Bert S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department

Inverness: Hydrology and Climatology

Description: Map showing various hydrologic and climatologic aspects (rainfall, measurement stations, hurricane inundation zones, etc.) in the Inverness region of the Florida coastline. Scale 1:100,000.
Date: 1984
Creator: U.S. Fish and Wildlife Service
Item Type: Refine your search to only Map
Location: None
Partner: UNT Libraries Government Documents Department

Inverness: Socioeconomic Features

Description: Map showing various sites and features (recreation sites, land use, landfills, historic sites, transportation, etc.) in the Inverness region of the Florida coastline. Scale 1:100,000.
Date: 1984
Creator: U.S. Fish and Wildlife Service
Item Type: Refine your search to only Map
Location: None
Partner: UNT Libraries Government Documents Department
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Investigation and Preparation of Polymer Films to Improve the Separation of Water and Salts in Saline Water Conversion

Description: From Introduction: "As will be explained in more detail elsewhere in this report, casting methods and drying conditions have been found to have a drastic effect on film permeability to both water and salt. Errors that became evident in temperature control indicated that some of the previous high rates were obtained at temperatures considerably higher than the 100 degrees C that was intended and reported."
Date: December 1962
Creator: Monsanto Research Corporation
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation at a Mach Number of 1.2 of Two 45 Degree Sweptback Wings Utilizing NACA 2-006 and NACA 65A006 Airfoil Sections

Description: Report presenting an investigation in the low-turbulence pressure tunnel at Mach number 1.2 to determine lift, drag, and moment characteristics of a wing with an airfoil section designed for maximum lift at low speeds, 45 degrees of sweepback, aspect ratio 4, and taper ratio 0.6. A similar wing with the NACA 65A006 airfoil section was also investigated and compared to the experimental wing.
Date: September 11, 1952
Creator: Wilson, Homer B., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation at a Mach number of 1.90 of a diverter-type boundary-layer removal system for a scoop inlet

Description: Report presenting an experimental investigation at Mach number 1.90 to determine the effect of a diverter-type boundary-layer removal system on the performance of a scoop inlet. The supersonic portion of the inlet consisted of a two-dimensional, reverse Prandtl-Meyer turn followed by a constant-area throat. Results regarding the effect of fuselage position and subsonic diffuser performance are provided.
Date: June 8, 1953
Creator: Kochendorfer, Fred D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation at a Mach Number of 1.93 to Determine Lift, Drag, Pitching-Moment, and Average Downwash Characteristics for Several Missile Configurations Having Rectangular Wings and Tails of Various Spans

Description: Memorandum presenting an investigation made at a Mach number of 1.93 to determine lift, drag, pitching-moment, and average downwash characteristics of several missile configurations. Five configurations with rectangular wings and tails of various spans were tested; each of the configurations had two locations of the wing relative to the tail.
Date: October 19, 1950
Creator: Grigsby, Carl E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation at high and low subsonic Mach numbers of two symmetrical 6-percent-thick airfoil sections designed to have high maximum lift coefficients at low speeds

Description: Report presenting an investigation at high and low subsonic Mach numbers of two symmetrical 6-percent-thick airfoil sections derived to have high maximum lift at low speeds. The high-speed portion of the investigation included lift, drag, and pitching moment measurements.
Date: October 17, 1952
Creator: Paradiso, Nicholas J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation at high subsonic speeds of a 45 sweptback horizontal tail with plain and horn-balanced control surfaces

Description: Report presenting an investigation in the 7- by 10-foot tunnel of the aerodynamic and hinge-moment characteristics of an untapered, aspect ratio 3, semispan horizontal-tail model with 45 degrees of sweepback through a range of Mach numbers. The model was equipped with an unbalanced and a horn-balanced 25-percent-chord elevator.
Date: March 31, 1950
Creator: Johnson, Harold S. & Thompson, Robert F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation at high subsonic speeds of a body-contouring method for alleviating the adverse interference at the root of a sweptback wing

Description: Report presenting an investigation of a body-contouring method for alleviating adverse interference of a high-aspect-ratio sweptback wing at high speeds. Modifying the body shape did not significantly affect the aerodynamic characteristics at subcritical speeds, but beneficial results were obtained at free-stream Mach numbers above critical. Results regarding force and pressure studies are provided.
Date: April 1956
Creator: McDevitt, John B. & Haire, William M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation at high subsonic speeds of bodies mounted from the wing of an unswept-wing-fuselage model, including measurements of body loads

Description: Report presenting an investigation with the dual purpose of determining the effect of two bodies in various positions, symmetrically located from the plane of symmetry, on the aerodynamic characteristics of a wing-fuselage model and determining the aerodynamic loads on one of two bodies. Some of the most significant effects were obtained for the direct-mounted tip bodies which gave a large increase in the lift-curve slope of the basic model.
Date: November 14, 1952
Creator: Silvers, H. Norman & King, Thomas J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation at high subsonic speeds of finned and unfinned bodies mounted at various locations from the wings of unswept- and swept-wing--fuselage models, including measurements of body loads

Description: Report presenting an investigation to determine the effects of location of bodies (finned and unfinned) on the aerodynamic characteristics of unswept- and swept-wing--fuselage models and to determine the aerodynamic loads on the bodies in the presence of the wings. Results for the complete model characteristics and for the body are provided.
Date: April 1, 1954
Creator: Alford, William J., Jr. & Silvers, H. Norman
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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