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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Strain gauge measuring techniques Patent
Strain gage measurement of elongation due to thermally and mechanically induced stresses
Internal flare angle gauge Patent
Gage for measuring internal angle of flare on end of tube
Piston manometer as an absolute standard for vacuum-gauge calibration
Piston manometer used as absolute standard for calibrating and intercomparing vacuum gages in 10 to 500 microtorr range
Results from a new wind-tunnel apparatus for studying coning and spinning motions of bodies of revolution
Wind tunnel apparatus for reproducing coning and spinning motions of bodies of revolution, using six-component strain gage balance for aerodynamic forces
New type of molecular mass gauge for use with small gas samples
Molecular mass gage with chambers interconnected by porous membranes for injected small gas samples
Elastic properties of the lunar surface from Surveyor spacecraft data
Elastic properties of lunar surface material from Surveyor spacecraft strain gage data
Mechanical compliance measurements of single- edge-notch tension specimens
Single edge notch tension Al alloy specimens mechanical compliance measurement, solving stress functions for various gage length-sample width combinations
Left and right ventricular pressures in mice
Transthoracic measurements of left and right ventricular systolic pressures in anesthetized mice, using fiber optics and strain gage manometer techniques
Computerized micromechanical testing
Materials microstrain determination using automatic capacitance bridge gage and analog or hybrid computer for measurement signal processing
Dynamic pressure measurements utilizing a cold-cathode ionization gauge
Cold cathode ionization gages dynamic pressure response as function of gas pulse mean speed and gas type, using magnetron test measurements
The dynamic characteristics of a five component oscillating balance
Frequency response of five component strain gage oscillating balance for dynamic wind tunnel stability testing
An in situ, metal-gas, secondary-standard assembly for ultrahigh-vacuum instrumentation
In situ metal-gas secondary standard assembly for ultrahigh vacuum gage calibration, using repeatable pressure generation from binary erbium- hydrogen system
The use of graphite in high and ultrahigh vacuum - A review
Graphite properties in high and ultrahigh vacuum, suggesting use as electrode material in vacuum gages and residual gas analyzers
Laboratory leak tester provides high sensitivity
Detecting unit is capable of measuring leak rates of 10 to the minus 5th power cc/sec or less. Device can be mounted in a carrying case and consists of three vacuum chambers, two pressure gages, and positive seal type control valves.
On the use of freon-12 for increasing Reynolds number in wind-tunnel testing of three dimensional aircraft models at subcritical and supercritical Mach numbers
The aerodynamic suitability of Freon-12 for general wind-tunnel testing was investigated at low and high subsonic speeds. Static aerodynamic characteristics of two transport airplane models were determined from strain gage balance measurements in both air and Freon-12 at several Reynolds numbers. A low-speed high-lift configuration was evaluated at Mach number 0.25, and a high-speed cruise wing-fuselage combination was tested at Mach numbers up to 0.825. The data obtained in air and in Freon-12 agree well, even in stalled flow, until compressibility effects evidently become significant in air and in Freon-12 agree well, even in stalled flow, until compressibility effects evidently become significant in air.
Structural efficiencies of five compression panels with curved elements
Structural-efficiency analyses are used to determine the minimum-mass proportions of some panel configurations loaded in uniaxial compression. Five panel constructions, four of which incorporate circular-arc elements and the other a beaded-web corrugation, are shown to have improved structural efficiencies over conventional configurations. In addition to the structural-efficiency equations, which give the mass equivalent flat-plate thickness of the panel necessary to carry a given load, related design equations for calculating the cross-sectional dimensions of these minimum-mass panels are presented. The upper and lower limits of loading, where the design constraints of minimum gage or material yield strength become the dominant design conditions, are established and the corresponding design equations which are applicable outside these limits are also presented.
Automated preliminary design of simplified wing structures to satisfy strength and flutter requirements
A simple structural model of an aircraft wing is used to show the effects of strength (stress) and flutter requirements on the design of minimum-weight aircraft-wing structures. The wing is idealized as an isotropic sandwich plate with a variable cover thickness distribution and a variable depth between covers. Plate theory is used for the structural analysis, and piston theory is used for the unsteady aerodynamics in the flutter analysis. Mathematical programming techniques are used to find the minimum-weight cover thickness distribution which satisfies flutter, strength, and minimum-gage constraints. The method of solution, some sample results, and the computer program used to obtain these results are presented. The results indicate that the cover thickness distribution obtained when designing for the strength requirement alone may be quite different from the cover thickness distribution obtained when designing for either the flutter requirement alone or for both the strength and flutter requirements concurrently. This conclusion emphasizes the need for designing for both flutter and strength from the outset.