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Model Study of Plans for Channel Improvement at Dogtooth Bend, Mississippi River, Folder 1

Description: This memorandum, constitutes a report on the results of experiments conducted at the U. S. Waterways Experiment Station on a small scale model of that reach of the Mississippi River near and including Dogtooth Bend (Mile 32.7 above to Mile 4.0 below Cairo).
Date: April 2, 1938
Creator: Waterways Experiment Station (U.S.)
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

General Theory of Aerodynamic Instability and the Mechanism of Flutter

Description: "The aerodynamic forces on an oscillating airfoil or airfoil-aileron combination of three independent degrees of freedom were determined. The problem resolves itself into the solution of certain definite integrals, which were identified as Bessel functions of the first and second kind, and of zero and first order. The theory, based on potential flow and the Kutta condition, is fundamentally equivalent to the conventional wing section theory relating to the steady case" (p. 291).
Date: May 2, 1934
Creator: Theodorsen, Theodore
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department

[Postcard with a love message and a woman's image]

Description: A postcard with a love message on one side and an image of a woman on the other. The woman's image is tinted pink and has been printed over with additional colors in multiple spots. "Feliz Recuardo" is written in gold above the woman. The love message on the postcard's back is printed in red and is positioned between handwritten words and numbers.
Date: July 2, 1938
Creator: Parlee, Lorena, 1945-2006
Item Type: Refine your search to only Photograph
Partner: UNT Libraries Special Collections
open access

The Effect of Continuous Weathering on Light Metal Alloys Used in Aircraft

Description: "An investigation of the corrosion of light metal alloys used in aircraft was begun at the National Bureau of Standards in 1925 and has for its purpose causes of corrosion in aluminum-rich and magnesium-rich alloys together with the development of methods for its prevention. The results, obtained in an extensive series of laboratory and weather-exposure tests, reveal the relative durability of a number of commercially available materials and the extent to which the application of various surfac… more
Date: December 2, 1938
Creator: Mutchler, Willard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Cooling of airplane engines at low air speeds

Description: Report presents the results of a comprehensive experimental study carried out at full scale in the NACA 20-foot wind tunnel, the general purpose of which is to furnish information in regard to the functioning of the power plant and propeller unit under different conditions. This report deals particularly with the problem of the cooling of an airplane engines on the ground. The influence of different nose forms, skirts, flaps, propellers, spinners, and special blowers has been investigated.
Date: June 2, 1936
Creator: Theodorsen, Theodore; Brevoort, M. J. & Stickle, George W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Lift and drag characteristics and gliding performance of an autogiro as determined in flight

Description: From Summary: "This report presents the results of flight test of the Pitcairn "PCA-2" autogiro. Lift and drag coefficients with the propeller stopped have been determined over approximately a 90 degree range of angles of attack. Based on the sum of fixed-wing and swept-disk areas, the maximum lift coefficient is 0.895, the minimum drag coefficient with propeller stopped is 0.015, and the maximum l/d with propeller stopped is 4.8. Lift coefficients were found also with the propeller delivering … more
Date: May 2, 1932
Creator: Wheatley, John B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Determination of the theoretical pressure distribution for twenty airfoils

Description: This report gives the theoretical distribution of pressure at lift coefficients of 0, 0.5, 1.0, and 1.5 for 20 airfoils, calculated on the basis of a rigorous potential theory of arbitrary airfoils. It also provides tables from which the characteristics of the airfoils for any angle of attack in 2-dimensional potential flow are readily calculable. The theoretical values of the angles of zero lift, the lift and moment coefficients, and the ideal angles of attack are listed and some comparisons w… more
Date: June 2, 1933
Creator: Garrick, I. E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Pressure distribution over a symmetrical airfoil section with trailing edge flap

Description: "Measurements were made to determine the distribution of pressure over one section of an R. A. F. 30 (symmetrical) airfoil with trailing edge flaps. In order to study the effect of scale measurements were made with air densities of approximately 1 and 20 atmospheres. Isometric diagrams of pressure distribution are given to show the effect of change in incidence, flap displacement, and scale upon the distribution. Plots of normal force coefficient versus angle of attack for different flap displa… more
Date: April 2, 1930
Creator: Jacobs, Eastman N. & Pinkerton, Robert M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The drag characteristics of several airships determined by deceleration tests

Description: This report presents the results of deceleration tests conducted for the purpose of determining the drag characteristics of six airships. The tests were made with airships of various shapes and sizes belonging to the Army, the Navy, and the Goodyear-Zeppelin Corporation. Drag coefficients for the following airships are shown: Army TC-6, TC-10, and TE-2; Navy Los Angeles and ZMC-2; Goodyear Puritan. The coefficients vary from about 0.045 for the small blunt airships to 0.023 for the relatively l… more
Date: March 2, 1931
Creator: Thompson, F. L. & Kirschbaum, H. W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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