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 Collection: Technical Report Archive and Image Library
Results of Assays of the New Albany Oil-Shale

Results of Assays of the New Albany Oil-Shale

Date: June 1923
Creator: Reeves, John R.
Description: Report issued by the U.S. Bureau of Mines on a survey of the New Albany oil-shale deposits in Indiana. The experimental procedures for surveying and sampling these shale deposits are presented in detail. This report includes tables, and graphs.
Contributing Partner: UNT Libraries Government Documents Department
Results of ATR Sample Fuel Plate Irradiation Experiment

Results of ATR Sample Fuel Plate Irradiation Experiment

Date: March 23, 1964
Creator: Phillips Petroleum Company
Description: From abstract: "Fuel materials proposed for use in the Advanced Test Reactor were evaluated."
Contributing Partner: UNT Libraries Government Documents Department
Results of axial-load fatigue tests on electropolished 2024-T3 and 7075-T6 aluminum-alloy-sheet specimens with central holes

Results of axial-load fatigue tests on electropolished 2024-T3 and 7075-T6 aluminum-alloy-sheet specimens with central holes

Date: March 1, 1956
Creator: Landers, Charles B & Hardrath, Herbert F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Results of edge-compression on stiffened flat-sheet panels of alclad and nonclad 14S-T6, 24S-T3, and 75S-T6 aluminum alloys

Results of edge-compression on stiffened flat-sheet panels of alclad and nonclad 14S-T6, 24S-T3, and 75S-T6 aluminum alloys

Date: April 1, 1954
Creator: Holt, Marshall
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Results of Electrical Resistivity and Electrical Induction Measurements at Abana Mine, Quebec, Canada: Explanation of Some Factors Associated with Induction Method

Results of Electrical Resistivity and Electrical Induction Measurements at Abana Mine, Quebec, Canada: Explanation of Some Factors Associated with Induction Method

Date: 1931
Creator: Potter, E. Vernon & Lee, F. W.
Description: Technical paper issued by the Bureau of Mines over studies conducted on electrical resistivity at the Abana Mine in Quebec. The methods used, and results of the studies are discussed. This paper includes tables, maps, and illustrations.
Contributing Partner: UNT Libraries Government Documents Department
Results of experimental flights at high altitudes with Daimler, Benz and Maybach engines to determine mixture formation and heat utilization of fuel

Results of experimental flights at high altitudes with Daimler, Benz and Maybach engines to determine mixture formation and heat utilization of fuel

Date: January 1, 1923
Creator: Kutzbach, K
Description: The experimental flights described herein were made with the object of obtaining information regarding the following two questions, which as yet have not been sufficiently elucidated. These are: 1. What effect has altitude upon the formation of the mixture? 2. What alteration takes place, with increasing altitude, in the utilization of the heat contained in the fuel?.
Contributing Partner: UNT Libraries Government Documents Department
Results of experiments with slotted wings

Results of experiments with slotted wings

Date: October 1, 1924
Creator: Lachmann, G
Description: This report recounts some of the successful experiments conducted in England and Germany on slotted wings and ailerons. Wind tunnel test results are given and examples of aircraft constructed with these new wing components are described.
Contributing Partner: UNT Libraries Government Documents Department
Results of extended tests of the Focke-Wulf F 19a "ente," a tail-first airplane

Results of extended tests of the Focke-Wulf F 19a "ente," a tail-first airplane

Date: September 1, 1933
Creator: Hubner, Walter
Description: These investigations consisted chiefly of measurements of the take-off distance under various starting conditions and with the c.g. in different positions; of the climbing speed as a function of the impact pressure and location of the c.g.; of the longitudinal stability and fore-and-aft controllability and of the determination of the elevator forces and characteristics of the elevator control.
Contributing Partner: UNT Libraries Government Documents Department
Results of Flight Test of an Automatically Stabilized Model C (Swept Back) Four-Wing Tiamat

Results of Flight Test of an Automatically Stabilized Model C (Swept Back) Four-Wing Tiamat

Date: June 11, 1947
Creator: Seacord, Charles L., Jr. & Teitelbaum, J. M.
Description: The results of the first flight test of a swept-back four-wing version of Tiamat (MX-570 model C) which was launched at the NACA Pilotless Aircraft Research Station at W4110PB Island, Va. are presented. In general, the flight behavior was close to that predicted by calculations based an stability theory and oscillating table tests of the autopilot. The flight test thus indicates that the techniques employed to predict automatic stability are valid and practical from an operational viewpoint. The limitations of the method used to predict flight behavior arise from the fact that the calculations assume no coupling among roll, pitch, and yaw, while in actual flight some such coupling does exist.
Contributing Partner: UNT Libraries Government Documents Department
Results of flight tests at supersonic speeds to determine the effect of body nose fineness ratio on body and wing drag

Results of flight tests at supersonic speeds to determine the effect of body nose fineness ratio on body and wing drag

Date: June 26, 1947
Creator: Katz, Ellis R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Results of flight tests to determine drag of parabolic and cone-cylinder bodies of very large fineness ratios at supersonic speeds

Results of flight tests to determine drag of parabolic and cone-cylinder bodies of very large fineness ratios at supersonic speeds

Date: August 30, 1951
Creator: Welsh, Clement J & Demoraes, Carlos A
Description: Results of a free-flight investigation at supersonic speeds to determine zero-lift drag of a series of bodies of revolution are presented. Configurations tested included two parabolic bodies with fineness ratios of 17.78 and 24.5 and two 8 degree cone-cylinder bodies with fineness ratios of 17.2 and 21.2. Results of previous tests of similar parabolic bodies but with lower fineness ratios are included in this paper for comparison. All bodies for which data are presented in this paper had a base-to-maximum-diameter ratio of 0.437. Calculated drag coefficients are shown for all bodies for which data are presented. (author).
Contributing Partner: UNT Libraries Government Documents Department
Results of flight tests to determine the drag of finite-length cylinders at high Reynolds numbers for a Mach number range of 0.5 to 1.3

Results of flight tests to determine the drag of finite-length cylinders at high Reynolds numbers for a Mach number range of 0.5 to 1.3

Date: June 16, 1952
Creator: Welsh, Clement J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Results of free-flight test of 1/10-scale model of the Convair XF2Y-1 airplane between Mach numbers of 0.7 and 1.45, including power-on flight at Mach number 1.2 : TED No. NACA DE 365

Results of free-flight test of 1/10-scale model of the Convair XF2Y-1 airplane between Mach numbers of 0.7 and 1.45, including power-on flight at Mach number 1.2 : TED No. NACA DE 365

Date: February 4, 1954
Creator: Bland, William M , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Results of initial wind-tunnel flutter experiments at low speed with a towed airplane model having a 40 degree sweptback wing of aspect ratio 3.62 equipped with pylon-mounted stores

Results of initial wind-tunnel flutter experiments at low speed with a towed airplane model having a 40 degree sweptback wing of aspect ratio 3.62 equipped with pylon-mounted stores

Date: March 24, 1955
Creator: Martina, Albert P & Young, George E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Results of landing tests of various airplanes

Results of landing tests of various airplanes

Date: September 1, 1942
Creator: Hootman, J A & Jones, A R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Results of measurements made during the approach and landing of seven high-speed research airplanes

Results of measurements made during the approach and landing of seven high-speed research airplanes

Date: February 4, 1955
Creator: Stillwell, Wendell H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Results of measurements of maximum lift and buffeting intensities obtained during flight investigation of the Northrop X-4 research airplane

Results of measurements of maximum lift and buffeting intensities obtained during flight investigation of the Northrop X-4 research airplane

Date: August 20, 1953
Creator: Baker, Thomas F
Description: The variation of the intensity of buffeting experienced throughout the operational region of the semitailless Northrop X-4 airplane and the values of maximum and peak normal-force coefficients in the Mach number range from 0.42 to 0.92 have been determined. The results are compared with data obtained with the swept-wing Douglas D-558-II airplane.
Contributing Partner: UNT Libraries Government Documents Department
Results of preliminary flight investigation of aerodynamic characteristics of the NACA two-stage supersonic research model RM-1 stabilized in roll at transonic and supersonic velocities

Results of preliminary flight investigation of aerodynamic characteristics of the NACA two-stage supersonic research model RM-1 stabilized in roll at transonic and supersonic velocities

Date: March 19, 1947
Creator: Pitkin, Marvin; Garner, William N & Curfman, Howard J , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Results of Preliminary Flight Tests of the XS-1 Airplane (8-Percent Wing) to a Mach Number of 1.25

Results of Preliminary Flight Tests of the XS-1 Airplane (8-Percent Wing) to a Mach Number of 1.25

Date: April 6, 1948
Creator: Williams, W C & Beeler, De E
Description: Presents results of the U. S. Air Forces' accelerated transonic flight tests of the XS-1 No. 1 airplane for the Mach number range from 0.70 to 1.25 at altitudes from 30,000 to 49,000 feet. Data are included on horizontal-tail loads and buffeting, longitudinal trim changes, elevator effectiveness and control forces, and lateral trim characteristics.
Contributing Partner: UNT Libraries Government Documents Department
Results of Primary Triangulation and Primary Traverse: Fiscal Year 1902-03

Results of Primary Triangulation and Primary Traverse: Fiscal Year 1902-03

Date: 1903
Creator: Gannett, Samuel S.
Description: From introduction: This report contains the results of the primary triangulation and primary traverse executed by the USGS during the fiscal year 1902-3.
Contributing Partner: UNT Libraries Government Documents Department
Results of Primary Triangulation and Primary Traverse: fiscal year 1903-04

Results of Primary Triangulation and Primary Traverse: fiscal year 1903-04

Date: 1904
Creator: Gannett, Samuel S.
Description: From introduction: This report contains the results of primary triangulation and primary traverse in the eastern and western divisions of the United States.
Contributing Partner: UNT Libraries Government Documents Department
Results of recent experiments with slotted wings

Results of recent experiments with slotted wings

Date: January 1, 1925
Creator: Lachmann, G
Description: This report gives the results of a recent series of experiments performed on a wing designed for a cantilever monoplane. Both wings were trapezial in their ground plan, with their tips rounded elliptically. These wing sections combine all known devices for increasing the lift, namely, the slot, the increased camber and angle of attack by means of an aileron running the whole length of the span. The last advance included in the wing section was an increase in wing area by means of an auxiliary wing adjusted by a sort of rectangular joint.
Contributing Partner: UNT Libraries Government Documents Department
Results of rocket model test of an airplane configuration having an arrow wing and slender flat-sided fuselage : lift, drag, longitudinal stability, lateral force, and jet effects at Mach numbers between 1.0 and 2.3

Results of rocket model test of an airplane configuration having an arrow wing and slender flat-sided fuselage : lift, drag, longitudinal stability, lateral force, and jet effects at Mach numbers between 1.0 and 2.3

Date: February 21, 1956
Creator: Peck, Robert F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Results of shear fatigue tests of joints with 3/16-inch-diameter 24S-T31 rivets in 0.064-inch-thick alclad sheet

Results of shear fatigue tests of joints with 3/16-inch-diameter 24S-T31 rivets in 0.064-inch-thick alclad sheet

Date: February 1, 1950
Creator: Holt, Marshall
Description: None
Contributing Partner: UNT Libraries Government Documents Department