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Knowledge Gained From Practical Experience in the Designing of Aircraft Engines

Description: The present report examines a few important points of engine design such as: in-line water cooled engines, air-cooled in-line engines, and air-cooled radial engines. Subassemblies are also discussed like cylinder types, blower driving gears, pistons, valves, bearings, and crankshafts.
Date: May 1933
Creator: Kurtz, Oskar
Partner: UNT Libraries Government Documents Department

A New Dynamometer Brake

Description: The mechanism here described belongs to the class of dynamometer brake in which the motive power is transformed into heat in the brake itself. This mechanism was invented by the writer for the purpose of measuring forces in which the two factors, torque and speed, vary within broad limits, the mechanism itself being of simple construction and of still simpler operation.
Date: September 1921
Creator: Segrè, Marco
Partner: UNT Libraries Government Documents Department

Load Assumptions for Calculating the Strength of Airplanes

Description: "The following load assumptions shall be taken as the basis of the strength calculations. Certain definite load conditions (e.g. of flight, control, landing and transport) shall be assumed. The loads shall be assumed to be safe loads, constant or only slowly variable, and the inertia forces due to elastic deformation are accordingly disregarded. The external forces, the force of gravity and the inertia forces on the whole airplane shall produce a condition of equilibrium" (p. 1).
Date: September 1930
Partner: UNT Libraries Government Documents Department

Research and Design Problems Introduced by Increased Power Output

Description: In what follows the question of the number and geometrical arrangement of the cylinders so important in the design of high performance power units will be considered from various points of view. A discussion will be given of the possibilities of the various working processes and an investigation will be made of possible means for improving the continuous operation and take-off performance, particularly the methods of supercharging, increasing the r.p.m., and employing the two-stroke-cycle engine. Finally, the question of lowered fuel consumption will be gone over briefly.
Date: October 1937
Creator: Kurtz, Oskar
Partner: UNT Libraries Government Documents Department

Effect of Exhaust Back Pressure on Engine Power

Description: Report presenting data on the effect of exhaust back pressure on engine power for 14 aircraft engines. The data showed that the effect of exhaust back pressure on engine power varies with engine speed, range of back pressure and manifold pressure involved, and engine type. The only method of accurately determining the effect of back pressure on engine power than can currently be recommended is to test the specific engine type at the engine speed for which data are desired.
Date: June 1943
Creator: Pinkel, Benjamin
Partner: UNT Libraries Government Documents Department

Some Altitude Operational Characteristics of a Prototype Iroquois Turbojet Engine, COORD. NO. AF-P-6

Description: The evaluation of the altitude operational characteristics was part of the over-all investigation of the early developmental Iroquois engine. Engine steady-state windmilling characteristics were evaluated over a range of flight Mach numbers from 0.48 to 1.72 at altitudes of 35,000 and 50,000 feet. Engine altitude ignition limits were obtained over a range of flight Mach numbers from 0.5 to 1.5 with the standard engine ignition system and also with an oxygen boost system. A short investigation of high-speed altitude reignition following combustor blowout was conducted.
Date: June 17, 1958
Creator: Peters, Daniel J. & McAulay, John E.
Partner: UNT Libraries Government Documents Department

Design and Test of Mixed-Flow Impellers 2: Experimental Results, Impeller Model MFI-1A

Description: An investigation was conducted to determine the performance characteristics of a mixed-flow impeller which was designed with special emphasis on the reduction or elimination of flow decelerations along wetted surfaces. The performance was investigated over a range of equivalent impeller speeds from 700 to 1600 feet per second and over a range of flow rates from maximum adiabatic temperature-rise efficiency, measured at 1-1/2 impeller diameters in a vaneless diffuser, at the design speed of 1400 feet per second were 4.00 and 0.83, respectively.
Date: September 19, 1952
Creator: Withee, Joseph R., Jr. & Beede, William L.
Partner: UNT Libraries Government Documents Department

Evaluation of Scavenging in Two-Stroke-Cycle Engines

Description: The viewpoints are discussed, according to which the scavenging of two-stroke-cycle engines can be evaluated, and the relations between scavenging pressure and the quantity of the scavenging medium required, as also between the scavenging pressure and the revolution speed, are developed. It is further shown that the power increase is limited by the scavenging process, so that further researches are desirable for qualitative improvement. These results lead to several conclusions regarding the propulsion of motor vehicles by the two-stroke-cycle engines.
Date: January 1934
Creator: Venediger, Herbert J.
Partner: UNT Libraries Government Documents Department

Comparison of Turbojet-Engine Altitude Performance Characteristics and Ignition Limits With MIL-F-5624A Fuel, Grades JP-3 and JP-4

Description: The performance of MIL-F-5624A fuels, grades JP-3 and JP-4, was investigated in an axial-flow turbojet engine over a range of altitude conditions of 10,000 to 55,000 feet. Examination of the fuel flow, combustion efficiency, and net thrust specific fuel consumption showed the grade JP-4 fuel to be slightly inferior to the grade JP-3 fuel, although the altitude ignition limits were essentially equal for the two fuels over a range of flight Mach numbers and fuel-inlet temperatures.
Date: February 27, 1952
Creator: Braithwaite, Willis M. & Renas, Paul E.
Partner: UNT Libraries Government Documents Department

Summary Report on Analytical Evaluation of Air and Fuel Specific-Impulse Characteristics of Several Nonhydrocarbon Jet-Engine Fuels

Description: Memorandum presenting an analytical evaluation of the air and fuel specific-impulse characteristics of magnesium, magnesium-octene-1 slurries, aluminum, aluminum-octene-1 slurries, boron, boron-octene-1 slurries, carbon, hydrogen, methylnaphthalene, diborane, and pentaborane. Adiabatic constant-pressure combustion temperature, air specific impulse, fuel specific impulse, and equilibrium composition data are given for each fuel over a range of equivalence ratios.
Date: February 19, 1953
Creator: Breitwieser, Roland; Gordon, Sanford & Gammon, Benson
Partner: UNT Libraries Government Documents Department

Two-Stage Supercharging

Description: "The arrangement of the parts and the installation and control problems of the two-stage mechanically driven superchargers for aircraft engines are discussed. Unless an entirely new form of supercharging is developed, there will be a definite need for a two-stage centrifugal supercharger. It is shown that the two-stage mechanically driven supercharger itself is a comparatively simple device; the complications arise from the addition of inter-coolers and controls" (p. 1).
Date: February 1941
Creator: Buck, Richard S.
Partner: UNT Libraries Government Documents Department

The Power of Aircraft Engines at Altitude

Description: The subject of the present paper is confined to the investigations and methods employed by the Fiat company in their studies on the altitude performance of an air-cooled engine of the production type. The experimental set-up as well as test engine data are provided.
Date: May 1939
Creator: Ragazzi, Paolo
Partner: UNT Libraries Government Documents Department

Correcting Horsepower Measurements to a Standard Temperature

Description: This report discusses the relation between the temperature of the air at the entrance to the carburetor and the power developed by the engine. Its scope is limited to a consideration of the range of temperatures likely to result from changes of season, locality, or altitude, since its primary aim is the finding of a satisfactory basis for correcting power measurements to a standard temperature. From the results of over 1,600 tests it is concluded that if calculations be based on the assumption that the indicated horsepower of an engine varies inversely as the square root of the absolute temperature of the carburetor air the values obtained will check closely experimental measurements.
Date: 1925
Creator: Sparrow, Stanwood W.
Partner: UNT Libraries Government Documents Department

Effect of Angle of Attack and Exit Nozzle Design on the Performance of a 16-Inch Ram Jet at Mach Numbers From 1.5 to 2.0

Description: "An investigation of the performance of a 16-inch ram jet engine having a single oblique-shock all-external compression inlet designed for a flight Mach number of 1.8, was conducted in the NACA Lewis 8-by 6-foot supersonic wind tunnel. Data were obtained at Mach numbers from 1.5 to 2.0 and angles of attack from 0 degrees to 10 degrees. Three exit nozzles were used; a cylindrical extension of the combustion chamber, a 4 degrees half-angle converging nozzle with a 0.71 contraction ratio, and a graphite converging-diverging nozzle having a 0.71 contraction ratio plus reexpansion to essentially major body diameter" (p. 1).
Date: October 5, 1951
Creator: Perchonok, Eugene; Wilcox, Fred & Pennington, Donald
Partner: UNT Libraries Government Documents Department

Observations on the Method of Determining the Velocity of Airships

Description: To obtain the absolute velocity of an airship by knowing the speed at which two routes are covered, we have only to determine the geographical direction of the routes which we locate from a map, and the angles of routes as given by the compass, after correcting for the variation (the algebraical sum of the local magnetic declination and the deviation).
Date: June 1921
Creator: Volterra, Vito
Partner: UNT Libraries Government Documents Department

The Factors That Determine the Minimum Speed of an Airplane

Description: The author argues that because of a general misunderstanding of the principles of flight at low speed, there are a large number of airplanes that could be made to fly several miles per hour slower than at present by making slight modifications. In order to show how greatly the wing section affects the minimum speed, curves are plotted against various loadings. The disposition of wings on the airplane slightly affects the lift coefficient, and a few such cases are discussed.
Date: March 1921
Creator: Norton, F. H.
Partner: UNT Libraries Government Documents Department

The Design of Jet Pumps

Description: This report shows that by applying both energy and impulse theorems the optimum throat dimension of the mixing nozzle and the best shape of intake can be predicted approximately in a relatively simple manner. The necessary length of the mixing nozzle follows from Prandtl's turbulent mixing theory. The calculations are carried out for the mixing of similar and dissimilar fluids.
Date: July 1941
Creator: Flügel, Gustav
Partner: UNT Libraries Government Documents Department

Effect of Valve Overlap and Compression Ratio on Variation of Measured Performance With Exhaust Pressure of Aircraft Cylinder and on Computed Performance of Compound Power Plant

Description: Note presenting an investigation conducted on an aircraft liquid-cooled single-cylinder test engine equipped with direct fuel injection to determine the effect of valve overlap and compression ratio on variation of engine power and specific fuel consumption with exhaust pressure. Results regarding the experimental engine data and compound-power-plant performance are provided.
Date: February 1950
Creator: Eian, Carroll S.
Partner: UNT Libraries Government Documents Department

Possible Improvements in Gasoline Engines

Description: High-compression engines are investigated with the three main objects being elimination of vibration, increase of maximum efficiency, and conservation of this efficiency at the highest possible speeds.
Date: January 1923
Creator: Ziembinski, S.
Partner: UNT Libraries Government Documents Department

The effects of hub drag, solidity, dual rotation, and number of blades upon the efficiency of high-pitch propellers

Description: Report presenting an investigation of the effects of hub drag, solidity, dual rotation, and number of blades on the efficiency of high-pitch propellers. Testing occurred with two, three, four, and six-blade single propellers and four and six-blade dual-rotating propellers equipped with spinners and tested at a range of blade angles from 35 to 65 degrees. Results regarding a comparison of the large and small spinners, effects of spinners, comparison of constant-speed propellers, characteristics of constant-speed propellers, effect of solidity and dual rotation, effect of number of blades, and some peculiarities of four-blade propellers are provided.
Date: October 1941
Creator: Reid, Elliott G.
Partner: UNT Libraries Government Documents Department

Correlation of effects of fuel-air ratio, compression ratio, and inlet-air temperature on knock limits of aviation fuels

Description: Report presenting a method of relating the effects of fuel-air ratio on the knock-limited charge flow and power of a supercharged engine with those of compression ratio and inlet-air temperature. Knock data obtained in a CFR engine over a wide range of conditions were correlated with eight fuels: 28-R fuel, aviation alkylate, S reference fuel, diisopropyl, triptane, cyclohexane, cyclopentane, and triptene.
Date: April 1950
Creator: Tower, Leonard K. & Alquist, Henry E.
Partner: UNT Libraries Government Documents Department