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UNT Libraries Government Documents Department
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National Advisory Committee for Aeronautics Collection
Abnormal grain growth in M-252 and S-816 alloys
Date: November 1, 1957
Creator: Decker, R F
Description: An experimental investigation was carried out on air- and vacuum-melted M-252 and S-816 alloys to find conditions of heating and hot-working which resulted in abnormal grain growth. The experiments were mainly limited to normal conditions of heating for hot-working and heat treatment and normal temperatures of solution treatment were used to allow grain growth after susceptibility to abnormal grain growth was developed by various experimental conditions. Results indicated that small reductions of essentially strain-free metal were the basic cause of such grain growth.
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc57131/
Abnormal grain growth in nickel-base heat-resistant alloys
Date: December 1, 1957
Creator: Decker, R F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc57096/
Abnormal grain growth in S-816 alloy
Date: April 1, 1952
Creator: Rush, A I
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc57000/
Absolute coefficients and the graphical representation of airfoil characteristics
Date: June 1, 1921
Creator: Munk, Max
Description: It is argued that there should be an agreement as to what conventions to use in determining absolute coefficients used in aeronautics and in how to plot those coefficients. Of particular importance are the absolute coefficients of lift and drag. The author argues for the use of the German method over the kind in common use in the United States and England, and for the Continental over the usual American and British method of graphically representing the characteristics of an airfoil. The author notes that, on the whole, it appears that the use of natural absolute coefficients in a polar diagram is the logical method for presentation of airfoil characteristics, and that serious consideration should be given to the advisability of adopting this method in all countries, in order to advance uniformity and accuracy in the science of aeronautics.
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc53725/
Absolute dimensions of Karman vortex motion
Date: January 1, 1923
Creator: Heisenberg, Werner
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc53809/
Absorbing landing shocks
Date: August 1, 1923
Creator: Warner, Edward P
Description: Tires, steel springs, hydraulic shock absorbers, and axle travel are all examined in relation to absorbing landing shocks.
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc56246/
Abstracts pertaining to seaplanes
Date: July 24, 1947
Creator: Bidwell, Jerold M
Description: About 400 references pertaining to the hydrodynamic design of seaplanes have been compiled, and the information is presented in the form of abstracts classified under six main headings.
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc62825/
Acceleration characteristics of a turbojet engine with variable-position inlet guide vanes
Date: July 7, 1955
Creator: Dobson, W F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc60813/
Acceleration Characteristics of R-3350 Engine Equipped with NACA Injection Impeller
Date: January 8, 1947
Creator: Hickel, Robert O.
Description: Qualitative investigations have shown that use of the NACA injection impeller with the R-3350 engine increases the inertia of the fuel-injection system and, when the standard fuel-metering system is used, this increase in inertia results in poor engine acceleration characteristics. This investigation was therefore undertaken to determine whether satisfactory acceleration characteristics of the engine equipped with the injection impeller could be obtained by simple modifications to the fuel-monitoring system. The engine was operated with two types of carburetor; namely, a hydraulic-metering carburetor incorporating a vacuum-operated accelerating pump and a direct-metering carburetor having a throttle-actuated accelerating pump. The vacuum-operated accelerating pump of the hydraulic-metering carburetor was modified to produce satisfactory accelerations by supplementing the standard air chamber with an additional 75-cubic spring. The throttle-actuated accelerating pump of the direct-metering carburetor was modified to produce satisfactory accelerations by replacing the standard 0.028-inch-diameter bleed in the load-compensator balance line with a smaller bleed of 0.0225-inch diameter. The results of this investigation indicated that both carburetors can be easily modified to produce satisfactory acceleration characteristics of the engine and no definite choice between the types of carburetor and accelerating pump can be made. Use of the direct-metering carburetor, however, probably resulted in better fuel ...
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc63808/
Acceleration Measurements During Landing in Rough Water of a 1/7-Scale Dynamic Model of Grumman XJR2F-1 Amphibian - Langley Tank Model 212, TED No. NACA 2378
Date: May 6, 1947
Creator: Land, Norman S.
Description: Tests of a 1/7 size model of the Grumman XJR2F-1 amphibian were made in Langley tank no.1 to examine the landing behavior in rough water and to measure the normal and angular accelerations experienced by the model during these landings. All landings were made normal to the direction of wave advance, a condition assumed to produce the greatest accelerations. Wave heights of 4.4 and 8.0 inches (2.5 and 4.7 ft, full size) were used in the tests and the wave lengths were varied between 10 and 50 feet (70 and 350 ft, full size). Maximum normal accelerations of about 6.5g were obtained in 4.4 inch waves and 8.5g were obtained in 8.0 inch waves. A maximum angular acceleration corresponding to 16 radians per second per second, full size, was obtained in the higher waves. The data indicate that the airplane will experience its greatest accelerations when landing in waves of about 20 feet (140 ft, full size) in length.
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc64281/