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Aerodynamic Factors Affecting the Ability of a Pilot to Return an Airplane to Level From a Banked Attitude by Use of the Rudder Alone and Without Change of Heading

Description: Report presenting a study of the aerodynamic factors upon which the ability to perform the maneuver depends in an attempt to obtain a better understanding of the conditions involved and, if possible, to evolve criterions that may be used during design.
Date: October 1941
Creator: Harmon, S. M.
Partner: UNT Libraries Government Documents Department

High-Altitude Cooling 6: Axial-Flow Fans and Cooling Power

Description: Report presenting the theory, design, and effect on cooling of the constant-velocity axial-flow fan as related to the problem of high-altitude aircraft engine cooling. The existing theory of the axial-flow fan, including a discussion of the fan losses, is summarized.
Date: September 1944
Creator: Mutterperl, William
Partner: UNT Libraries Government Documents Department

The Oxidation of Exhaust Gases at Room Temperature

Description: Report presenting an investigation made to determine the effectiveness of various oxides and oxide mixtures in oxidizing at room temperature the exhaust gases from an internal-combustion engine for the determination of fuel-air ratio. The oxides of silver, copper, manganese, cobalt, nickel, iron, cerium, lead, bismuth, and mercury were tested individually and in various combinations.
Date: February 1945
Creator: Gerrish, Harold C.; Meem, J. Lawrence, Jr. & Tuck, Vivian C.
Partner: UNT Libraries Government Documents Department

Measurements of Friction Coefficients in a Pipe for Subsonic and Supersonic Flow of Air

Description: Report presenting tests of the flow of air through brass tubes with the friction coefficient and incompressible flow relation as the main focus. The analytical relation between friction coefficient, tube length, and Mach number is shown for flow without shock and the conditions for flow with and without shock are delimited.
Date: July 1943
Creator: Keenan, Joseph H. & Neumann, Ernest P.
Partner: UNT Libraries Government Documents Department

A Method of Calculating Bending Stresses Due to Torsion

Description: Report presenting a method for analyzing bending stresses due to torsion in a box with variable cross section and loading by means of a recurrence formula leading to a set of equations identical in form with the well-known three-moment equations. An approximate form of the general method of analysis is presented that eliminates the need of solving a system of equations.
Date: December 1942
Creator: Kuhn, Paul
Partner: UNT Libraries Government Documents Department

A Method for Welding Sheet Aluminum to SAE 4140 Steel

Description: Report presenting an investigation of a large variety of different metals used as an intermediate metal between aluminum and steel for the purpose of securing a good bond both from the viewpoint of strength and thermal conductivity. The principal result was that it was found possible to secure a satisfactory bond between aluminum and steel by electroplating the steel with a layer of silver of proper thickness.
Date: January 1944
Creator: Hess, W. F. & Nippes, E. F., Jr.
Partner: UNT Libraries Government Documents Department

Method of Calculating Performance of Dual-Rotating Propellers From Airfoil Characteristics

Description: "A method is developed for calculating the performance of a dual-rotating propeller from the section characteristics of the blade elements. The method is applied to an eight-blade dual-rotating propeller and the computed results are compared with low-speed wind-tunnel tests of the same propeller in both the tractor and pusher positions. The computations are found to agree within the experimental accuracy of the measurements" (p. 1).
Date: May 1943
Creator: Naiman, Irven
Partner: UNT Libraries Government Documents Department

A Method for Making Quantitative Studies of the Main Spray Characteristics of Flying-Boat Hull Models

Description: Report presenting a method and apparatus for making quantitative tests of the spray characteristics of flying-boat-hull models. The method is applied to three related models of flying-boat hulls which differed in one major characteristic of shape: the overall dead rise.
Date: November 1943
Creator: Locke, F. W. S., Jr.
Partner: UNT Libraries Government Documents Department

A Method for Studying the Longitudinal Dynamic Stability of Flying-Boat-Hull Models at High Planing Speeds and During Landing

Description: Report presenting an investigation of a method of studying the longitudinal dynamic stability of flying-boat-hull models, as instability may be encountered when flying a flying boat on the water at high speeds and high trim angles, especially upper-limit porpoising and skipping. A method is described for carrying out generalized experimental studies of the longitudinal dynamic stability of flying-boat-hull models.
Date: April 1945
Creator: Locke, F. W. S., Jr. & Hugli, W. C., Jr.
Partner: UNT Libraries Government Documents Department

Procedure Used at Aluminum Research Laboratories for Determining Type of Attack in Some Aluminum Alloys

Description: Report presenting samples of 17S-T and 24S-T aluminum alloys subjected to accelerated corrosion tests in which the corrosion period was established at 6 hours for samples that had been etched to produce a uniform surface. The results indicate the types of corrosion attack, which are described in standard terminology, and may form a basis for estimating the resistance of the material to corrosion by a comparison of the relative depth and frequency of the corrosive attacks.
Date: August 1942
Creator: Walton, C. J. & Keller, F.
Partner: UNT Libraries Government Documents Department

Preliminary Tank Tests With Planing-Tail Seaplane Hulls

Description: Report presenting testing made with simplified models of two types of hulls that differ considerably from conventional types. Both have a single main planing surface that is combined with after-planing surfaces placed directly below the aerodynamic tail surfaces. Results regarding an investigation of twin planing tails, a single-planing tail, and potentialities indicated by tests are provided.
Date: June 1943
Creator: Dawson, John R. & Waldin, Kenneth L.
Partner: UNT Libraries Government Documents Department

Airfoil-Contour Modifications Based on (Epsilon)-Curve Method of Calculating Pressure Distribution

Description: From Introduction: "Certain alternations of a qualitative nature may be performed in spite of the fact that a pressure change cannot be prescribed. It is the purpose of this paper to indicate a method by which qualitative alternation may be performed. It will be noted that the present method of contour modification will serve the intended purpose of the inverse method."
Date: July 1944
Creator: Theodorsen, Theodore
Partner: UNT Libraries Government Documents Department

An Investigation of Aircraft Heaters 5: Theory and Use of Heat Meters for the Measurement of Rates of Heat Transfer Which Are Independent of Time

Description: Report presenting a description of a meter which will measure the heat flowing through surfaces. Its operation is based on the measurement of the temperature decrease through a fixed thermal resistance. Only the case of heat flow independent of time is discussed in this particular report.
Date: December 1942
Creator: Martinelli, R. C.; Morrin, E. H. & Boelter, L. M. K.
Partner: UNT Libraries Government Documents Department

An Investigation of Aircraft Heaters 2: Properties of Gases

Description: Report presenting the properties of some exhaust gases and air that are pertinent to airplane heat transfer calculations, including air, hydrogen, nitrogen, oxygen, carbon dioxide, and carbon monoxide. A bibliography related to gas properties is also provided.
Date: October 1942
Creator: Tribus, Myron & Boelter, L. M. K.
Partner: UNT Libraries Government Documents Department

Flight Measurements of the Elevator Deflections Used in Landings of Several Airplanes

Description: "A collection of data on the elevator deflections used in landings of several airplanes is presented in tabular form. The physical characteristics of these airplanes are also given. The elevator deflections used in landing some airplanes was found to be as much as 14.4 degrees greater than that used to stall under the same flight and loading conditions" (p. 1).
Date: November 1941
Creator: Vensel, Joseph R.
Partner: UNT Libraries Government Documents Department

Flight Studies of the Horizontal-Tail Loads Experienced by a Fighter Airplane in Abrupt Maneuvers

Description: Report presenting flight measurements made on a modern pursuit airplane to determine the approximate magnitude of the horizontal tail loads in accelerated flight. Pressures at a few points were used as an index of the tail loads by correlating these pressures with complete pressure-distribution data obtained in the NACA full-scale tunnel.
Date: June 1944
Creator: Flight Research Maneuvers Section
Partner: UNT Libraries Government Documents Department

Full-Scale Wind-Tunnel Investigation of Forward Underslung Cooling-Air Ducts

Description: Report presenting an investigation of underslung cooling-air ducts in various locations on a model of a typical single-engine tractor airplane in the full-scale tunnel. The report contains the results of tests of two forward underslung ducts. Results regarding pressure recoveries at the radiator, pressures behind the radiator, drag and duct efficiency, and critical speeds are provided.
Date: October 1944
Creator: Nelson, W. J.; Czarnecki, K. R. & Harrington, Robert D.
Partner: UNT Libraries Government Documents Department

Fuel Consumption Corrected for Cooling Drag of an Air-Cooled Radial Aircraft Engine at Low Fuel-Air Ratios and With Variable Spark Advance

Description: Report presenting results of tests conducted with an air-cooled, radial aircraft engine to determine the reduction in the brake specific fuel consumption that would result from operating with a very low fuel-air ratio and an increased spark advance. Computed values of the brake specific fuel consumption corrected for cooling-air drag are also given.
Date: February 1945
Creator: Munger, Maurice
Partner: UNT Libraries Government Documents Department

The Flow of a Compressible Fluid Past a Circular Arc Profile

Description: Report presenting the use of the Ackeret iteration process to obtain higher approximations than that of Prandtl and Glauert for the flow of a compressible fluid past a circular arc profile. The procedure is to expand the velocity potential in a power series of the camber coefficient.
Date: October 1944
Creator: Kaplan, Carl
Partner: UNT Libraries Government Documents Department

High-Altitude Cooling 2: Air-Cooled Engines

Description: Report presenting the heat-transfer theory for air-cooled engines and an analysis of the cooling pressure drop for the case in which the pressure drop is an appreciable fraction of the absolute pressure. A chart is given for the simple determination of the cooling pressure drop predicted on the basis of the usual type of sea-level cooling-correlation tests.
Date: September 1944
Creator: Williams, David T.
Partner: UNT Libraries Government Documents Department