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An investigation of aircraft heaters 22: measured and predicted performance of a fluted-type exhaust gas and air heat exchanger

Description: Report presenting data on the thermal performance and static and total pressure drop characteristics of a fluted-type exhaust gas and air heat exchanger. Results regarding heat transfer, pressure drop, and non-isothermal pressure drop are provided.
Date: April 1945
Creator: Boelter, L. M. K.; Guibert, A. G.; Rademacher, J. M. & Romie, F. E.
Partner: UNT Libraries Government Documents Department
open access

An investigation of aircraft heaters 23: measured and predicted performance of a flat-plate type exhaust gas and air heat exchanger

Description: Report presenting results of tests of the thermal performance and the static pressure drop characteristics of a flat-plate type exhaust gas and air heat exchanger. The ventilating air shroud built into the heat exchanger gives characteristics of cross flow and parallel flow.
Date: April 1945
Creator: Boelter, L. M. K.; Guibert, A. G.; Rademacher, J. M. & Sanders, V. D.
Partner: UNT Libraries Government Documents Department
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An Investigation of Aircraft Heaters 21: Measured and Predicted Performance of a Flattened-Tube Type Crossflow Exhaust Gas and Air Heat Exchanger

Description: Report presenting data on the thermal performance and the static pressure drop characteristics of a flattened-tube type crossflow exhaust gas and air heat exchanger. The measured thermal outputs and static pressure drops are compared with predicted magnitudes.
Date: April 1945
Creator: Boelter, L. M. K.; Guibert, A. G.; Rademacher, J. M.; Romie, F. E.; Sanders, V. D. & Sloggy, L. J. B.
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation of a Rectangular NACA 2212 Airfoil with Semispan Ailerons and with Nonperforated, Balanced Double Split Flaps for Use as Aerodynamic Brakes

Description: Flat-plate flaps with no wing cutouts and flaps having Clark Y sections with corresponding cutouts made in wing were tested for various flap deflections, chord-wise locations, and gaps between flaps and airfoil contour. The drag was slightly lower for wing with airfoil section flaps. Satisfactory aileron effectiveness was obtained with flap gap of 20% wing chord and flap-nose location of 80 percent wing chord behind leading edge. Airflow was smooth and buffeting negligible.
Date: April 1945
Creator: Ivey, Margaret F. & Toll, Thomas A.
Partner: UNT Libraries Government Documents Department
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A Method for Determining Oil-Cooler Performance Requirements in Series Operation

Description: Report presenting an equation by which the overall performance of any number of oil coolers when operating in series can be related to their performance when operating singly. A comparison was made of the experimental overall performance of two conventional type 15-inch-diameter oil coolers, selected according to the analysis and equipped first with spring-loaded valves and then with rotary valves, with the desired overall performance.
Date: September 1945
Creator: Boyet, H.
Partner: UNT Libraries Government Documents Department
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Standard Method of Graphical Presentation of Centrifugal Compressor Performance

Description: Report on the NACA recommended method for comparing the performance of centrifugal compressors. The most important indices of compressor performance are the adiabatic temperature rise ratio or adiabatic efficiency, the adiabatic shaft efficiency, and the pressure ratio, which incorporate many other parameters. Recommendations for reporting on compressor effectiveness and characteristics are provided.
Date: August 1945
Creator: NACA Subcommittee on Supercharger Compressors
Partner: UNT Libraries Government Documents Department
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Performance Effect of Fully Shrouding a Centrifugal Supercharger Impeller

Description: Report presenting a program of tests to determine the effect of an integral front shroud on the performance characteristics of a centrifugal supercharger impeller. The impellers tested included a modification of a commercial semishrouded impeller and a fully shrouded impeller, which was the same as the semishrouded one except for an integral front shroud.
Date: October 1945
Creator: Ritter, William K. & Johnsen, Irving A.
Partner: UNT Libraries Government Documents Department
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Performance Characteristics of Journal Bearings With Forced-Feed Lubrication

Description: "Friction and heat-dissipation data are presented for use in determining the load-carrying capacity of 2- by 1.25-inch bearings with the following types of lining: copper-lead, lead-indium-coated silver, and lead-coated copper-lead. The tests were made in a four-bearing friction machine and covered operation with three clearances using three oils of different viscosity at three oil-inlet temperatures. Values are computed to indicate the safe loads at various speeds for bearings lined with each … more
Date: August 1944
Creator: McKee, S. A.; White, H. S.; Bell, A. D. & Swindells, J. F.
Partner: UNT Libraries Government Documents Department
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Study of the Mixture Distribution of a Double-Row Radial Aircraft Engine

Description: "A test-stand investigation was conducted to determine the mixture distribution of a conventional double-row radial engine for a wide range of engine speeds, powers, and fuel-air ratios and to evaluate its effect on engine performance. The fuel was injected into the combustion-air stream by a rotating spray ring located near the impeller entrance. Fuel-air ratios of the individual cylinders were determined from chemical analyses of the exhaust gas" (p. 1).
Date: October 1945
Creator: Marble, Frank E.; Butze, Helmut F. & Hickel, Robert O.
Partner: UNT Libraries Government Documents Department
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Effect of Coaxial Lapping of Cast-Iron Piston Rings on Ring Performance

Description: Report presenting a series of 25-hour accelerated high-output tests run on a single-cylinder aircraft-type spark-ignition engine to determine the effect of coaxial lapping of piston rings prior to engine operation. Standard cast-iron rings were used and tested with all rings lapped and with only the oil-control rings lapped. The results indicated that coaxial lapping with loose abrasive reduced both wear and scuffing.
Date: April 1944
Creator: Shames, Sidney J.; Machlin, Eugene S. & Wilson, John G.
Partner: UNT Libraries Government Documents Department
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Tests of Thermal-Electric De-Icing Equipment for Propellers

Description: "Flights were made in natural icing conditions at the NACA Ice Research Project, Minneapolis, Minn. to test several designs of thermal-electric propeller de-icing blade shoes and a hub-generator design. It was found that a minimum average unit power of 2.5 watts per square inch of blade-shoe area would protect the propeller blades at the test conditions. The most satisfactory blade shoe of the three designs tested extended to the 20-percent-chord point and to 90 percent of the blade radius" (p.… more
Date: January 1944
Creator: Scherrer, Richard & Rodert, Lewis A.
Partner: UNT Libraries Government Documents Department
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Tests of Improvements in Exhaust-Valve Performance Resulting From Changes in Exhaust-Valve and Port Design

Description: Report discusses the results of tests on single-cylinder engines to determine the worth of several changes in exhaust-valve and port design to extend the useful life of the valves used in air-cooled engines. Changes explored included the valve-head diameter, the valve-stem diameter, the valve coolant-flow area, the valve-head material, and the size of the exhaust-valve guide boss. In the normal range of temperatures encountered in engine operation, valve material was found to be the most import… more
Date: September 1945
Creator: Mulcahy, B. A. & Zipkin, M. A.
Partner: UNT Libraries Government Documents Department
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A Correlation of the Effects of Compression Ratio and Inlet-Air Temperature on the Knock Limits of Aviation Fuels in a CFR Engine 2

Description: Report presenting the knock-limited performance of nine fuels comprising isolated members of four classes of hydrocarbons in the form of three-dimensional plots of fuel-air ratio, compression temperature, and compression-air density.
Date: June 1946
Creator: Alquist, Henry E.; O'Dell, Leon & Evvard, John C.
Partner: UNT Libraries Government Documents Department
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Knock-limited performance of pure hydrocarbons blended with a base fuel in a full-scale aircraft-engine cylinder 2: twelve aromatics

Description: Report presenting an investigation of the knock-limited performance of leaded blends of 12 pure aromatic hydrocarbons in a full-scale aircraft-engine cylinder at CRC simulated cruise and take-off conditions to determine the antiknock effectiveness of additions of pure compounds to aviation fuels. Results indicated that all of the hydrocarbons increased the knock limit of the base fuel except for 2 of them.
Date: September 1944
Creator: Bull, Arthur W. & Jones, Anthony W.
Partner: UNT Libraries Government Documents Department
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Knock-limited performance of pure hydrocarbons blended with a base fuel in a full-scale aircraft-engine cylinder 3: four aromatics, six ethers

Description: Report presenting knock-limited performance tests of leaded blends of four pure aromatic hydrocarbons and six pure ethers with a base fuel in a full-scale aircraft-engine cylinder at two operating conditions to determine the antiknock effectiveness of additions of pure compounds to aviation fuels.
Date: March 1946
Creator: Jones, Arthur W.; Bull, Arthur W. & Jonash, Edmund R.
Partner: UNT Libraries Government Documents Department
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Graphical representation of intercooler parameters and performance at altitudes from 25,000 to 60,000 feet

Description: From Summary: "Interdependence of intercooler parameters and performance for a pursuit-type airplane using a 1675-horsepower engine is shown at altitudes of 25,000, 36,000, 47,000, and 60,000 feet by means of perspective drawings. Qualitatively, the drawings have general application. Intercooling between stages of supercharging at high altitudes results in no saving in the power to supercharge and cool the engine air."
Date: November 1942
Creator: Brimley, D. E.
Partner: UNT Libraries Government Documents Department
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Performance tests of NACA type A finned-tube exhaust heat exchanger

Description: Report presenting tests to determine the thermal and pressure-drop performance and durability of a cross-flow, internally finned, tubular exhaust-heat exchanger. The test covered a range of exhaust-gas flows, cooling-air flows, and exhaust-gas temperatures.
Date: August 1944
Creator: Reuter, J. George & Manson, S. V.
Partner: UNT Libraries Government Documents Department
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Effect of Aromatics and Spark Advance on Thermal Efficiency

Description: Report presenting an analysis of experimental and theoretical data, which indicates that critical evaluation of fuel performance, especially economy, must be made in the engine. Data show that heating value is, from the aspect of fuel economy, not so important an aviation-fuel specification as believed. The knock ratings of fuels are affected by spark advance.
Date: September 1942
Creator: Gilbert, Mitchell
Partner: UNT Libraries Government Documents Department
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