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1 - 24 of
19,681
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Analysis of Wind-Tunnel Stability and Control Tests in Terms of Flying Qualities in Full-Scale Airplanes
From Summary: "The analysis of results of wind-tunnel stability and control tests of powered airplane models in terms of the flying qualities of full-scale airplanes is advocated. In order to indicate the topics upon which comments are considered desirable in the report of a wind-tunnel stability and control investigation and to demonstrate the nature of the suggested analysis, the present NACA flying-qualities requirements are discussed in relation to wind-tunnel tests. General procedures for the estimation of flying qualities from wind-tunnel tests are outlined."
Date:
October 1943
Creator:
Kayten, Gerald G.
Object Type:
Report
System:
The UNT Digital Library
The Measurement of Fuel-Air Ratio by Analysis for the Oxidized Exhaust Gas
"An investigation was made to determine a method of measuring fuel-air ratio that could be used for test purposes in flight and for checking conventional equipment in the laboratory. Two single-cylinder test engines equipped with typical commercial engine cylinders were used. The fuel-air ratio of the mixture delivered to the engines was determined by direct measurement of the quantity of air and of fuel supplied and also by analysis of the oxidized exhaust gas and of the normal exhaust gas. Five fuels were used: gasoline that complied with Army-Navy fuel Specification No. AN-VV-F-781 and four mixtures of this gasoline with toluene, benzene, and xylene" (p. 1).
Date:
1943
Creator:
Gerrish, Harold C. & Meem, J. Lawrence, Jr.
Object Type:
Report
System:
The UNT Digital Library
The effect of compressibility on two-dimensional tunnel-wall interference for a symmetrical airfoil
Summary: The effective change in the velocity of flow past a wing section, caused by the presence of wind-tunnel walls, is known for potential flow. This theory is extended by investigation of the two-dimensional compressible flow past a thin Rankine Oval. It is shown that for a symmetrical section at zero angle of attack the velocity increment due to the tunnel walls in the incompressible case must be multiplied by the factor 1/1-M^2 to take account of compressibility effects. The Mach number, M, corresponds to conditions in the wind-tunnel test section with the model removed (p. 1.).
Date:
May 1943
Creator:
Nitzberg, Gerald E.
Object Type:
Report
System:
The UNT Digital Library
Emergency Measures for Increasing the Range of Fighter Airplanes
"An analysis was made to show the relative effectiveness of streamline external fuel tanks, a fuel tank in the form of a wing mounted in a biplane position, and auxiliary wing panels attached at the wing tips to increase the span as temporary means for increasing the range of a fighter-type airplane. Figures and charts for the various devices considered show the results of calculations of range, duration of flight, and take-off distance for both land-base and carrier operation. The results indicated that the wing-tip extensions were the most promising of the devices considered" (p. 1).
Date:
May 1943
Creator:
Jones, Robert T. & Wetmore, Joseph W.
Object Type:
Report
System:
The UNT Digital Library
Review of Flight Tests of NACA C and D Cowlings on the XP-42 Airplane
Report presenting the results of flight tests of the performance and cooling characteristics of three NACA D cowlings and of a conventional NACA C cowling on the XP-42 airplane. The D cowling is, generally, characterized by the use of an annular inlet and diffuser section for the engine-cooling air. An increase in maximum speed was noted in the XP-42 airplane due to the change from a C cowling to a D cowling.
Date:
April 1943
Creator:
Johnston, J. Ford
Object Type:
Report
System:
The UNT Digital Library
Flight tests of thermal ice-prevention equipment in the XB-24F airplane
Report presenting performance tests of thermal ice-prevention equipment designed and installed in the XB-24F airplane in icing and non-icing conditions. The recorded temperature and air-flow data, and the calculated quantities of heat flow throughout the system are presented in tabular form.
Date:
October 7, 1943
Creator:
Neel, Carr B. & Jones, Alun R.
Object Type:
Report
System:
The UNT Digital Library
NACA Mach number indicator for use in high-speed tunnels
Report presenting a description of a device for indicating stream Mach number in a high-speed tunnel. It consists of a mechanism for determining the pressure ratio that Mach number is a function of. The instrument is in service in the 8-foot high-speed tunnel and its accuracy has been found adequate for wind-tunnel requirements.
Date:
July 1943
Creator:
Smith, Norman F.
Object Type:
Report
System:
The UNT Digital Library
Ditching Tests With 1/10-Size Model of the Army a-20a Airplane 1: Calm-Water Tests in NACA Tank No.2
Report presenting tests to determine the behavior of landplanes when they are forced to land on the water. The report is incomplete.
Date:
November 1943
Creator:
Dawson, John R. & Jarvis, George A.
Object Type:
Report
System:
The UNT Digital Library
Flight Measurements of the Effect of Various Amounts of Aileron Droop on the Low-Speed Lateral-Control Characteristics of an Observation Airplane
Report presenting tests of the low-speed lateral-control characteristics of an observation airplane with ailerons and spoilers in combination and with the spoilers disconnected and the ailerons used alone with various amounts of droop. The results indicated that in unstalled flight at low speeds and with flaps deflected, little or no aerodynamic benefit was derived by changing the lateral-control system from the aileron and spoiler combination to a normal aileron installation either with or without aileron droop.
Date:
August 18, 1943
Creator:
Turner, William N.
Object Type:
Report
System:
The UNT Digital Library
Determination of General Relations for the Behavior of Turbulent Boundary Layers
Report presenting an analysis of data for turbulent boundary layers along wings and bodies of various shapes in order to determine the fundamental variables that control the development of turbulent boundary layers. Results indicate that the type of velocity distribution in the boundary layer could be expressed in terms of a single parameter.
Date:
July 1943
Creator:
von Doenhoff, Albert E. & Tetervin, Neal
Object Type:
Report
System:
The UNT Digital Library
An Investigation of Aircraft Heaters 9: Measured and Predicted Performance of Two Exhaust Gas-Air Heat Exchangers and an Apparatus for Evaluating Exhaust Gas-Air Heat Exchangers
Report presenting laboratory testing to determine the thermal output and pressure drop characteristics of the Airesearch and Solar fluted-type exhaust gas-air heat exchangers. The apparatus used in these tests consisted of a natural gas furnace of 3,000,000 Btu per hour thermal capacity, a centrifugal blower, and a system of ducting and various measuring devices. Results regarding the method of analysis, the Airesearch heat exchanger tests, the solar heat exchanger tests, and a comparison of the two heat exchangers are provided.
Date:
March 1943
Creator:
Boelter, L. M. K.; Miller, M. A.; Sharp, W. H.; Morrin, E. H.; Iversen, H. W. & Mason, W. E.
Object Type:
Report
System:
The UNT Digital Library
Thermodynamic Design of Double-Panel, Air-Heated Windshields for Ice Prevention
Report details the development of design equations for double-panel, air-heated windshields with ice prevention properties. The application of the equations and suggestions for experimental flight testing are described.
Date:
June 1943
Creator:
Kushnick, Jerome L.
Object Type:
Report
System:
The UNT Digital Library
A Method of Estimating the Knock Rating of Hydrocarbon Fuel Blend
"The usefulness of the knock ratings of pure hydrocarbon compounds would be increased if some reliable method of calculating the knock ratings of fuel blends was known. The purpose of this study was to investigate the possibility of developing a method of predicting the knock ratings of fuel blends" (p. 1).
Date:
1943
Creator:
Sanders, Newell D.
Object Type:
Report
System:
The UNT Digital Library
The effect of altitude on cooling
Report presenting variables that control the cooling of liquid-cooled and air-cooled engines and then to show by illustrations how either engine may be cooled at any desired altitude. Cooling was found to not be the limiting factor in the design of high-altitude airplanes and was also not found to be a valid reason for selecting either liquid- or air-cooled engines for high-altitude operation.
Date:
March 1943
Creator:
Brevoort, Maurice J.; Joyner, Upshur T. & Wood, George P.
Object Type:
Report
System:
The UNT Digital Library
The problem of longitudinal stability and control at high speeds
Report discussing the difficulty in pulling of high-speed dives, which is primarily due to the effect of compressibility on the lift of the wing. Some of the means described for providing increased longitudinal control include auxiliary flaps and a controllable stabilizer.
Date:
November 1943
Creator:
Hood, Manley J. & Allen, H. Julian
Object Type:
Report
System:
The UNT Digital Library
Notes on the Effect of Surface Distortions on the Drag and Critical Mach Number of Airfoils
"The effect of two-dimensional bumps and surface waviness on the pressure distribution over airfoils is considered. It is shown that the results of the analysis may be useful in evaluating the effects of accidental or intended surface distortions on the drag and critical Mach number of airfoils" (p. 1).
Date:
September 1943
Creator:
Allen, H. Julian
Object Type:
Report
System:
The UNT Digital Library
Derivation of charts for determining the horizontal tail load variation with any elevator motion
Report presenting equations relating the wing and tail loads are derived for a unit elevator displacement. The equations are converted into a nondimensoinal form and charts are given that can be used to predict wing- and tail-load-increment variation for any type of elevator motion and for degrees of airplane stability.
Date:
January 1943
Creator:
Pearson, Henry A.
Object Type:
Report
System:
The UNT Digital Library
Icing Tests of Aircraft-Engine Induction Systems
Report presenting a program of icing tests conducted on an aircraft-engine induction system consisting of a Wright R-1820, G-200 blower section, Holley 1375-F carburetor and adapter, and specially built air scoop. The primary purpose of the investigation was to determine the effect of a number of possible factors on icing of engine-induction systems, including carburetor-air temperature, air-moisture content, water-droplet size, throttle opening, mixture ratio, rate of air flow, altitude, and others.
Date:
January 1943
Creator:
Kimball, Leo B.
Object Type:
Report
System:
The UNT Digital Library
[Philip Price]
Photograph of basketball player Philip Price dribbling a basketball in uniform.
Date:
1943
Creator:
unknown
Object Type:
Photograph
System:
The UNT Digital Library
[J. D. Lane]
Photograph of J. D. Lane, a North Texas basketball player. He poses in his uniform, holding a basketball above his shoulder.
Date:
1943
Creator:
unknown
Object Type:
Photograph
System:
The UNT Digital Library
[Frances Higginbotham at a Counter]
Photograph of Frances Higginbotham, for the Who's Who in Library Service. She works at a wood desk or counter.
Date:
1943
Creator:
unknown
Object Type:
Photograph
System:
The UNT Digital Library
[Herman Hopkins]
Photograph of basketball player Herman Hopkins. He wears the team uniform and holds a basketball.
Date:
1943
Creator:
unknown
Object Type:
Photograph
System:
The UNT Digital Library
[Ray Leonard]
Photograph of Ray Leonard standing in front of a blackboard with writing in English and Greek. She holds a book in her hands, and appears to be addressing a class. In 1943, she was voted Who's Who of foreign languages.
Date:
1943
Creator:
unknown
Object Type:
Photograph
System:
The UNT Digital Library
[Photograph 2012.201.B0297.0212]
Photograph taken for a newspaper owned by the Oklahoma Publishing Company. Caption: "Everet E. Deater, Delaware-Aviation Cadet."
Date:
June 17, 1943
Creator:
unknown
Object Type:
Photograph
System:
The Gateway to Oklahoma History