National Advisory Committee for Aeronautics (NACA) - 1,171 Matching Results

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On the plane potential flow past a symmetrical lattice of arbitrary airfoils

Description: Report presenting a theoretical investigation of the two-dimensional, incompressible potential flow past a symmetrical lattice of airfoils of arbitrary shape. Expressions are given for evaluation of the velocity and pressure distribution at the airfoil boundary.
Date: January 1944
Creator: Garrick, I. E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Critical combinations of shear and transverse direct stress for an infinitely long flat plate with edges elastically restrained against rotation

Description: Report presenting an exact solution and a closely concurring approximate energy solution for the buckling of an infinitely long flat plate under combined shear and transverse direct stress with edges elastically restrained against rotation. An appreciable fraction of the critical stress in pure shear may be applied to the plate without any reduction in the transverse compressive stress necessary to produce buckling.
Date: January 1945
Creator: Batdorf, S. B. & Houbolt, John C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Armstrong Whitworth A.W. 16 Military Airplane (British): A Single-Seat Biplane

Description: Circular presenting a description of the A.W. XVI, which is a single-bay staggered biplane of metal construction with a clean external design. A description of the tail unit, control system, cockpit, fuselage, characteristics, performance, drawings, and photographs are provided.
Date: January 1932
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Unsteady Lift of a Finite Wing

Description: Note discussing the lift of a finite wing including the calculations and constants for each step of the lift. This information is compared against the lift of an infinite wing. From Summary: "Unsteady lift function for wings of finite aspect ratio have been calculated by approximate methods involving corrections of the aerodynamic inertia and of the angle of the infinite wing. The starting lift of the finite wing is found to be only slightly less than that of the infinite wing; whereas the fina… more
Date: January 1939
Creator: Jones, Robert T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A study of the use of various high-lift devices on the horizontal tail of a canard airplane model as a means of increasing the allowable center-of-gravity travel

Description: Report presenting an investigation to study the use of various high-lift devices on the horizontal tail of a canard airplane model as a means of increasing the allowable center-of-gravity travel. The results indicated that the large increases in allowable center-of-gravity travel could be obtained using the devices. Results regarding the basic aerodynamic data, effect of tail configuration on the allowable center-of-gravity travel, and a comparison of measured and predicted values of the allowa… more
Date: January 21, 1953
Creator: Johnson, Joseph L., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Compressible potential flow with circulation about a circular cylinder

Description: Report presenting the potential function for flow, with circulation, of a compressible fluid about a circular cylinder, which is obtained in series form including terms of the order of M(exp 4) where M is the Mach number of the free stream. The equations are used to obtain pressure coefficient as a function of Mach number at a point on the surface of the cylinder for different values of circulation.
Date: January 1944
Creator: Heaslet, Max A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Pressure drop in tank and float vent tubes on diving airplanes

Description: Report presenting an experiment regarding tank and float venting conditions that exist on diving airplanes undergoing rapid changes in altitude. The results indicated that large pressure differences build up between the outside and inside of tanks and floats on diving airplanes unless the correct size of venting tube is used.
Date: January 1939
Creator: Waldron, C. D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Dyle and Bacalan Metal Monoplane, D.B. 10: Night Bomber - Equipped with Two 420 HP. Jupiter Engines

Description: The D.B. 10 is manufactured of duraluminum and special high resistance steel. It can be used as a passenger aircraft or as a bomber. Details of the design, wings, fuselage, empennage, engines, landing gear, characteristics, performances, drawings, and photographs are provided.
Date: January 1927
Creator: Serryer, J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Derivation of charts for determining the horizontal tail load variation with any elevator motion

Description: 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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Icing Tests of Aircraft-Engine Induction Systems

Description: 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 o… more
Date: January 1943
Creator: Kimball, Leo B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Clerget 100 Hp Heavy-Oil Engine

Description: A complete technical description of the Clerget heavy-oil engine is presented along with the general characteristics. The general characteristics are: 9 cylinders, bore 120 mm, stroke 130 mm, four-stroke cycle engine, rated power limited to 100 hp at 1800 rpm; weight 228 kg; propeller with direct drive and air cooling. Moving parts, engine block, and lubrication are all presented.
Date: January 1931
Creator: Léglise, Pierre
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Combating Airplane Fires

Description: This report provides a summary of the important steps to be taken in combating airplane fires. Some considerations and ways of preventing fires from developing are provided.
Date: January 1930
Creator: Brunat, Henri
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Single-Cylinder Oil-Control Tests of Porous Chrome Plated Cylinder Barrels for Radial Air-Cooled Engines

Description: Report presenting a series of single-cylinder engine tests run to determine a satisfactory method of reducing oil consumption in radial air-cooled engines with flat-face compression rings as standard parts and equipped with cylinder barrels salvaged by porous chrome plating. Testing was conducted using porous chrome-plated cylinders with straight and choke bores with standard flat-face compression rings.
Date: January 1946
Creator: Johnson, Robert L. & Swikert, Max
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Preliminary Investigation of the Performance of a Short Length Turbojet Combustor Using Vaporized Hydrocarbon Fuels

Description: "Two short turbojet combustors designed for use with vaporized hydrocarbon fuels were tested in a one-quarter annular duct. The experimental combustors consisted of many small "swirl-can" combustor elements manifolded together. This design approach allowed the secondary mixing zone to be considerably reduced over that of conventional combustors" (p. 1).
Date: January 7, 1958
Creator: Jones, R. E. & Pawlik, E. V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental Investigation of Diffuser Pressure Ratio Control With Shock Positioning Limit on 28 Inch Ram-Jet Engine

Description: Report presenting an investigation of the performance of a diffuser static-pressure-ratio control with a normal shock-positioning limit on a ramjet engine installed in an altitude free-jet facility. Testing occurred at Mach numbers of 2.35 and 2.50, altitudes of 50,000, 60,000 and 65,000 feet, and angles of attack of 0 and 7 degrees. Results regarding the effects of control constants, effects of disturbance size and operating point, effects of flight conditions, and control limitations and poss… more
Date: January 15, 1957
Creator: Dunbar, William R.; Wentworth, Carl B. & Crowl, Robert J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Column and Plate Compressive Strengths of Aircraft Structural Materials: Extruded 0-1HTA Magnesium Alloy

Description: Column and plate compressive strengths of extruded 0-1HTA magnesium alloy were determined both within and beyond the elastic range from tests of flat end H-section columns and from local instability tests of H-, Z-, and channel section columns. These tests are part of an extensive research investigation to provide data on the structural strength of various aircraft materials. The results are presented in the form of curves and charts that are suitable for use in the design and analysis of aircr… more
Date: January 1947
Creator: Heimerl, George J. & Niles, Donald E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Corrosion tests of a heated wing utilizing an exhaust-gas-air mixture for ice prevention

Description: Report presenting an investigation of the exhaust of corrosive attack in an aluminum alloy wing employing an exhaust-gas-air mixture as a heating medium for ice prevention. There were no cases of structurally serious corrosion on either painted or plain specimens removed from the wing for detailed microscopic and metallurgic examination.
Date: January 1949
Creator: Holdaway, George H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Study by the Prandtl-Glauert method of compressibility effects and critical Mach number for ellipsoids of various aspect ratios and thickness ratios

Description: From Summary: "By the use of a form of the Prandtl-Glauert method that is valid for three-dimensional flow problems, the value of the maximum incremental velocity for compressible flow about thin ellipsoids at zero angle of attack is calculated as a function of the Mach number for various aspect ratios and thickness ratios. The critical Mach numbers (within the accuracy of the Prandtl-Glauert method) of the various ellipsoids are also determined. The results indicate an increase in critical Mac… more
Date: January 1949
Creator: Hess, Robert V. & Gardner, Clifford S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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