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  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
Synthetic Liquid Fuels from Hydrogenation of Carbon Monoxide: Cobalt and Iron Catalysts for the Fischer-Tropsch Synthesis: Preparation and Characterization of Catalysts, Synthesis Tests, and Reaction Mechanism (Part 2 of Two Parts)

Synthetic Liquid Fuels from Hydrogenation of Carbon Monoxide: Cobalt and Iron Catalysts for the Fischer-Tropsch Synthesis: Preparation and Characterization of Catalysts, Synthesis Tests, and Reaction Mechanism (Part 2 of Two Parts)

Date: 1959
Creator: Shultz, J. F.; Hofer, L. J. E.; Cohn, E. M.; Stein, K. C. & Anderson, R. B.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Synthetic resins in aircraft construction - their composition, properties, present state of development and application to light structures

Synthetic resins in aircraft construction - their composition, properties, present state of development and application to light structures

Date: November 1, 1937
Creator: Riechers, K
Description: This report gives a brief review of the properties that have been attained with the synthetic materials with which we are at present familiar. Results of investigations are presented as well as possibilities for construction applications. Endurance strength and bonding tests are also presented.
Contributing Partner: UNT Libraries Government Documents Department
Syphon diaphragms : a method for predicting their performance for purposes of instrument design

Syphon diaphragms : a method for predicting their performance for purposes of instrument design

Date: January 1, 1922
Creator: Eaton, H N & Keulegan, G H
Description: Here, the purpose is to show that the characteristic performance of a syphon diaphragm can be predicted from a knowledge of its stiffness and of its dimensions. The proof is based on a mathematical analysis of this type of diaphragm, together with enough experimental data to prove the validity of the assumptions and the sufficiency of the analysis. Equations are developed for the performance of syphons under various conditions of loading, both for concentrated loads and for hydrostatic pressure.
Contributing Partner: UNT Libraries Government Documents Department
System analyses and autopilot design for automatic roll stabilization of a supersonic pilotless aircraft

System analyses and autopilot design for automatic roll stabilization of a supersonic pilotless aircraft

Date: July 11, 1951
Creator: Zarovsky, Jacob
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A system for measuring the dynamic lateral stability derivatives in high-speed wind tunnels

A system for measuring the dynamic lateral stability derivatives in high-speed wind tunnels

Date: December 1, 1954
Creator: Lessing, Henry C; Fryer, Thomas B & Mead, Merrill H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A System for the Automatic Computation of Disintegration Rates From Radiochemical Data

A System for the Automatic Computation of Disintegration Rates From Radiochemical Data

Date: May 27, 1959
Creator: Collins, William R., Jr.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Systematic airfoil tests in the large wind tunnel of the DVL

Systematic airfoil tests in the large wind tunnel of the DVL

Date: March 1, 1938
Creator: Doetsch, H & Kramer, M
Description: The present report is a description of systematic tests at maximum lift on airfoils with and without split flap and of profile drag at low lift. In order to obtain an opinion as to the suitability of the airfoils with flaps, the maximum-lift measurements were repeated on airfoils with split flaps. The profile drag at low lift was arrived at by direct weighing and momentum measurements and, since the profiles were of unusual depth, extended to large Reynolds numbers.
Contributing Partner: UNT Libraries Government Documents Department
Systematic investigation of Joukowsky wing sections

Systematic investigation of Joukowsky wing sections

Date: July 1, 1927
Creator: Schrenk, O
Description: Ackeret began systematic polar measurements on Joukowsky wing sections, which were occasionally conducted in the wind tunnel. Under these conditions a considerable number of wing sections were tested during the last four years and the tests are now more or less concluded.
Contributing Partner: UNT Libraries Government Documents Department
A systematic investigation of pressure distributions at high speeds over five representative NACA low-drag and conventional airfoil sections

A systematic investigation of pressure distributions at high speeds over five representative NACA low-drag and conventional airfoil sections

Date: January 1, 1945
Creator: Graham, Donald J; Nitzberg, Gerald E & Olson, Robert N
Description: Pressure distributions determined from high-speed wind-tunnel tests are presented for five NACA airfoil sections representative of both low-drag and conventional types. Section characteristics of lift, drag, and quarter-chord pitching moment are presented along with the measured pressure distributions for the NACA 65sub2-215 (a=0.5), 66sub2-215 (a=0.6), 0015, 23015, and 4415 airfoils for Mach numbers up to approximately 0.85. A critical study is made of the airfoil pressure distributions in an attempt to formulate a set of general criteria for defining the character of high speed flows over typical airfoil shapes. Comparisons are made of the relative characteristics of the low-drag and conventional airfoils investigated insofar as they would influence the high-speed performance and the high-speed stability and control characteristics of airplanes employing these wing sections.
Contributing Partner: UNT Libraries Government Documents Department
Systematic Investigations of the Effects of Plan Form and Gap between the Fixed Surface and Control Surface on Simple Flapped Wings

Systematic Investigations of the Effects of Plan Form and Gap between the Fixed Surface and Control Surface on Simple Flapped Wings

Date: May 1, 1949
Creator: Goethert & Roeber
Description: Four component measurements of 12 wings of symmetric profile having flaps with chord ratios t(sub R)/t(sub L) = 0.3 and t(sub R)/t(sub L) = 0.2 are treated in this report. As a result of the investigations, the effects of plan form and gap between fixed surface and control surface have been clarified. Lift, drag, pitching moment, and hinge moment were measured in the control-surface deflection range: -23 deg < or = beta < or = 23 deg and the range of angle of attack: -20 deg < or = alpha < or = 20 deg. Six wings with flaps of small chord (t(sub R)/t(sub L) < 0.1) were investigated at large flap settings.
Contributing Partner: UNT Libraries Government Documents Department