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Results of a Biological Survey of Mount Shasta California

Description: From introduction: "Biological survey of northern California from the Madeline Plains to the Pacific Ocean and from the Oregon boundary to Lassen Butte and parts of the Sierra, with Mount Shasta occupying a nearly central position."
Date: October 28, 1899
Creator: Merriam, C. Hart
Partner: UNT Libraries Government Documents Department
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A Biological Survey of Alabama

Description: Booklet describing the biology of Alabama in two sections: (1) physiography and life zones, and (2) mammals. It also includes an annotated species list of mammals, bibliography, and index starting on page 81.
Date: October 28, 1921
Creator: Howell, Arthur H.
Partner: UNT Libraries Government Documents Department
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Brown Oxide by-product Recovery. Part V

Description: No Description Available.
Date: October 28, 1943
Creator: Barnes, J. W.; Copenhafer, D. R.; Furnas, T. C.; Opie, J. V. & Reid, G. C.
Partner: UNT Libraries Government Documents Department
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Shock Hydrodynamics and Blast Waves

Description: No Description Available.
Date: October 28, 1944
Creator: Bethe, H.A.; Fuchs, K.; von Neuman, J.; Peierls, R.; Penney, W.G. & Hirschfelder, notes written by J.O.
Partner: UNT Libraries Government Documents Department
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The Temperature Coefficient of the Diffusion Length for Thermal Neutrons in Water

Description: Abstract. The diffusion length of thermal neutrons in water as a function of the water temperature has been measured. The results are expressed as a linear relation: L = 2.644 + 0.0061T where L is the diffusion length in centimeters and T is the temperature in degrees centigrade.
Date: October 28, 1944
Creator: Wilson, V. C.; Bragdon, E. W. & Kanner, H.
Partner: UNT Libraries Government Documents Department
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Investigation of the performance of a 20-inch ram jet using preheated fuel

Description: Report presenting the performance characteristics of a 20-inch ramjet opeerating with preheated unleaded 62 octane fuel. The results of the investigation indicated an improvement in the combustion efficiency and operating range of the ramjet when using preheated fuel.
Date: October 28, 1946
Creator: Perchonok, Eugene; Wilcox, Fred A. & Sterbentz, William H.
Partner: UNT Libraries Government Documents Department
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Tables of Neutron Cross Sections

Description: Report presenting data tables which summarize neutron cross sections for elements from hydrogen to bismuth. This data was to be available on September 1, 1947. Purpose and acknowledgements are given as well as criteria for omitting measurements and explanation of the material.
Date: October 28, 1947
Creator: Way, Katharine & Haines, G.
Partner: UNT Libraries Government Documents Department
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Tables of Neutron Cross Sections

Description: No Description Available.
Date: October 28, 1947
Creator: Way, K. & Haines, G.
Partner: UNT Libraries Government Documents Department
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Aerodynamic Characteristics of Two All-Movable Wings Tested in the Presence of a Fuselage at a Mach Number of 1.9

Description: Report presenting testing of half-span models of two wings of different plan form as both all-movable and fixed surfaces in the presence of a half fuselage. All-movable surfaces are being considered for supersonic aircraft as possible angle-of-attack indicators, control surfaces, and all-movable wings. Results regarding the lift characteristics, center of pressure, and drag of the wings are provided.
Date: October 28, 1948
Creator: Conner, D. William
Partner: UNT Libraries Government Documents Department
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The Effect of Boundary-Layer Control by Suction and of Several High-Lift Devices on the Aerodynamic Characteristics in Yaw of a 47.5 Degree Sweptback

Description: An investigation has been made in the Langley full-scale tunnel of a 47.5 degree sweptback wing-fuselage combination equipped for boundary-layer control by suction. The wing aspect ratio was 3.5, the taper ratio was 0.5 and the airfoil sections normal to the quarter-chord line were NACA 61(sub 1)-A112. Tests included the plain wing and the wing with various combinations of extensible leading-edge and split flaps.
Date: October 28, 1948
Creator: Pasamanick, Jerome
Partner: UNT Libraries Government Documents Department
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Investigation of Low-Speed, Power-Off Stability and Control Characteristics of a Model With a 35 Degree Sweptback Wing in the Langley Free-Flight Tunnel

Description: Report presenting an investigation in the free-flight tunnel to determine the low-speed, power-off dynamic stability and control characteristics of a model with a 35 degree sweptback wing. The investigation consisted of force and flight tests of the model and calculations of the lateral oscillatory stability with wing-tip fuel tanks off and on.
Date: October 28, 1948
Creator: Schade, Robert O.
Partner: UNT Libraries Government Documents Department
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An Investigation of the Aerodynamic Characteristics of an 0.08-Scale Model of the Chance Vought XF7U-1 Airplane in the Langley High-Speed 7-by 10-Foot Tunnel: TED No. DE308, Part 6, Estimated High-Speed Flying Qualities

Description: "An analysis of the estimated high-speed flying qualities of the Chance Vought XF7U-1 airplane in the Mach number range from 0.40 to 0.91 has been made, based on tests of an 0.08-scale model of this airplane in the Langley high-speed 7- by 10-foot wind tunnel. The analysis indicates longitudinal control-position instability at transonic speeds, but the accompanying trim changes are not large. Control-position maneuvering stability, however, is present for all speeds. Longitudinal lateral control appear adequate, but the damping of the short-period longitudinal and lateral oscillations at high altitudes is poor and may require artificial damping" (p. 1).
Date: October 28, 1948
Creator: Donlan, Charles J. & Kuhn, Richard E.
Partner: UNT Libraries Government Documents Department
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A theoretical analysis of the effect of time lag in an automatic stabilization system on the lateral oscillatory stability of an airplane

Description: "A method is presented for determining the effect of time lag in an automatic stabilization system on the lateral oscillatory stability of an airplane. The method is based on an analytical-graphical procedure. The critical time lag of the airplane-autopilot system is readily determined from the frequency-response analysis. The method is applied to a typical present-day airplane equipped with an automatic pilot sensitive to yawing acceleration and geared to the rudder so that rudder control is applied in proportion to the yawing acceleration" (p. 1).
Date: October 28, 1949
Creator: Sternfield, Leonard & Gates, Ordway B., Jr.
Partner: UNT Libraries Government Documents Department
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Evaluation of operating characteristics of a supersonic free-jet facility for full-scale ram-jet investigations

Description: From Summary: "A supersonic free-jet facility (Mach number 3) capable of accommodating full-scale ram-jet engines has been constructed and evaluated. A 24-inch circular nozzle produces a jet of sufficiently uniform velocity that a good simulation of the engine internal flow is obtained. An annular diffuser placed around the engine recovers part of the total pressure of the jet flow passing outside the engine so that the pressure ratios which must be imposed across the facility to start and maintain the jet are kept to reasonable values."
Date: October 28, 1952
Creator: Wentworth, Carl B.; Hurrell, Herbert G. & Nakanishi, Shigeo
Partner: UNT Libraries Government Documents Department
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On Traveling Waves in Beams

Description: "The basic equations of Timoshenko for the motion of vibrating nonuniform beams, which allow for effects of transverse shear deformation and rotary inertia, are presented in several forms, including one in which the equations are written in the directions of the characteristics. The propagation of discontinuities in moment and shear, as governed by these equations, is discussed. Numerical traveling-wave solutions are obtained for some elementary problems of finite uniform beams for which the propagation velocities of bending and shear discontinuities are taken to be equal" (p. 359).
Date: October 28, 1952
Creator: Leonard, Robert W. & Budiansky, Bernard
Partner: UNT Libraries Government Documents Department
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Performance characteristics at Mach numbers to 2.0 of various types of side inlets mounted on fuselage of proposed supersonic airplane 4: rectangular cowl inlets with two-dimensional compression ramps

Description: Report presenting an experimental investigation to determine the performance of side inlets with external compression ramps and rectangular cowls mounted on the fuselage forebody of a proposed supersonic airplane. Results regarding supersonic Mach number range, subsonic Mach number of 0.63, and static or take-off conditions are provided.
Date: October 28, 1952
Creator: Simon, Paul C.
Partner: UNT Libraries Government Documents Department
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The Structure of Turbulence in Fully Developed Pipe Flow

Description: "Measurements, principally with a hot-wire anemometer, were made in fully developed turbulent flow in a 10-inch pipe at speeds of approximately 10 and 100 feet per second. Emphasis was placed on turbulence and conditions near the wall. The results include relevant mean and statistical quantities, such as Reynolds stresses, triple correlations, turbulent dissipation, and energy spectra" (p. 1).
Date: October 28, 1952
Creator: Laufer, John
Partner: UNT Libraries Government Documents Department
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Data on Spoiler-Type Ailerons

Description: Report presenting information about spoiler-type ailerons, which are of interest because they give high reversal speeds for the thin, flexible wings now used. A bibliography on spoiler-type controls is also provided.
Date: October 28, 1953
Creator: Lowry, John G.
Partner: UNT Libraries Government Documents Department
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INTRACELL FLUX TRAVERSES

Description: No Description Available.
Date: October 28, 1953
Creator: Kouts, Herbert
Partner: UNT Libraries Government Documents Department
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Recent Results Pertaining to the Application of the "Area Rule"

Description: "This paper is concerned primarily with the application of the "area rule" to the interpretation and improvement of the drag-rise characteristics of wing-body combinations at transonic and moderate supersonic speeds. Consideration of the general physical nature of the flow at transonic speeds, together with comparisons of the flow fields and drag-rise characteristics for wing-body combinations and bodies of revolution has led to the conclusion that near the speed of sound the drag rise for a thin low-aspect-ratio wing-body combination is primarily dependent on the axial distribution of cross-sectional area normal to the airstream (ref. 1). (The drag rise, sometimes referred to as pressure drag, is the difference between the drag level near the speed of sound and the drag level at subsonic speeds where the drag is due primarily to skin friction.) In order to illustrate the concept, figure 1 shows a wing-body combination and a body of revolution" (p. 1).
Date: October 28, 1953
Creator: Whitcomb, Richard T.
Partner: UNT Libraries Government Documents Department
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A transonic wind-tunnel investigation of the longitudinal stability and control characteristics of a 0.09-scale model of the Bell X-5 research airplane and comparison with flight

Description: Report presenting an investigation conducted in the 8-foot transonic tunnel to determine the longitudinal stability and control characteristics of a 0.09-scale model of the Bell X-5 research airplane. Lift, drag, pitching-moment, elevator hinge-moment, and pressure-distribution results are presented for a range of Mach and Reynolds numbers. Results regarding lift and drag characteristics, longitudinal stability and control characteristics, dynamic-response characteristics, elevator hinge-moment characteristics, and mass-flow characteristics and pressure distributions are provided.
Date: October 28, 1953
Creator: Bielat, Ralph P. & Campbell, George S.
Partner: UNT Libraries Government Documents Department
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Casting Astrolite Cylinders

Description: No Description Available.
Date: October 28, 1955
Creator: Oswald, L.
Partner: UNT Libraries Government Documents Department
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