New CW ion laser transitions in argon, krypton, and xenon
CW ion laser transitions in Ar, Kr and Xe, tabulating threshold data
Hodges, D. T.↗
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Results for “Tabulation”
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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Pulsar data tables
Pulsar data tabulation of positions, dispersion measures, and class I pulse periods and widths
Maran, S. P.↗
The brightness of the zodiacal light
Zodiacal light brightness measurement in three mutually perpendicular directions, tabulating data
Roosen, R. G.↗
A photometric study of V701 Centauri
Eclipsing variable V701 Cen photoelectric observations in UBV tabulated, fitting Russell model solutions to data
Chen, K.-Y.↗
SERT II - Mission, thruster performance, and in-flight thrust measurements
SERT 2 spacecraft ion thrustor ground tests and flight operation, tabulating performance data
Goldman, R. G.↗
Neutron star models including the effects of hyperon formation
Neutron star matter equations of state involving hyperon formation effects for maximal stable mass models, tabulating moments of inertia
Cameron, A. G. W.↗
A method of treating the nongray error in total emittance measurements
Total emittance measurements by portable IR reflectometer, tabulating nongray error effects
Heaney, J. B.↗
Calculation of the partition function for super 14 N sub 2 super 16 O
Nitrous oxide internal and rotational partition functions for temperature range 200 to 350 K, using molecular constants tabulated by Pliva
Young, L. D. G.↗
Three-track runway and taxiway profiles measured at International Airports E and F
Three-track runway and taxiway profiles are presented for use in studies of airplane response to ground roughness. This report presents the tabulated and plotted data for two international airports (designed airports E and F).
Hall, A. W.↗
XB-70 aerodynamic, geometric, mass, and symmetric structural mode data
XB-70-1 mass, structural, and aerodynamic data were updated to reflect as closely as possible the characteristics of the airplane at three specific flight conditions which were actually flown; a nominal Mach number of 0.90 at an altitude of 25,000 feet (two cases) and a nominal Mach number of 1.6 at an altitude of 40,000 feet (one case). In-flight response characteristics at a number of points on the vehicle were obtained by exciting a pair of shaker vanes on the nose of the airplane. Data were recorded with the basic stability augmentation system (SAS) operating both alone and together with the identical location of accelerometer and force (ILAF) structural mode control system. Detailed total vehicle weight, mass characteristics, structural frequencies, generalized masses, all aerodynamic data used in the present analyses, and a description of the actual mode shapes are tabulated and presented.
Wykes, J. H.↗
Ground noise measurements during landing, take-off, and flyby operations of a four-engine turbopropeller STOL airplane
Noise measurements were obtained for a four-engine turbopropeller STOL airplane during a Federal Aviation Administration flight evaluation program at the National Aviation Facilities Experimental Center. These noise measurements involved landing-approach, takeoff-climbout, and flyby operations of the airplane. A total of 13 measuring positions were used to define the noise characteristics around a simulated STOL port. The results are presented in the form of both physical and subjective measurements. An appendix is included to present tabulated values of various subjective reaction units which may be significant for the planning and operation of STOL ports. The main source of noise produced by this vehicle was found to be the propeller, and noise levels decrease generally in accordance with the inverse-distance law for distances up to about 457 meters. For similar slant ranges, somewhat lower noise levels were experienced during flyby than during takeoff or landing.
Hilton, D. A.↗
Space shuttle: Heat transfer rate measurements on Convair booster (B-15B-2) and North American Rockwell orbiter (161B) at nominal Mach number of 8
Plotted and tabulated data from the thin-skin thermocouple phase of an experimental test program are presented. These data are representative of three events of simulated flight and are described as booster-orbiter ascent heating data, booster reentry heating data, and orbiter reentry heating data. The test was conducted in a 50-inch hypersonic tunnel b at a nominal Mach number of 8 and free-stream Reynolds number range of 700,000 to 3,700,000 per foot. The model employed was a 0.009 scale replica of the Convair B-15B-2 booster and North American Rockwell 161B orbiter.
Warmbrod, J. D.↗
Laboratory evaluation of Fecker and Loral optical IR PWI systems
A previous flight test of two electro-optical pilot warning indicators, using a flashing xenon strobe and silicon detectors as cooperative elements, pointed out several design deficiencies. The present laboratory evaluation program corrected these faults and calibrated the sensitivity of both systems in azimuth elevation and range. The laboratory tests were performed on an optical bench and consisted of three basic components: (1) a xenon strobe lamp whose output is monitored at the indicator detector to give pulse to pulse information on energy content at the receiver; (2) a strobe light attenuating optical system which is calibrated photometrically to provide simulated range; and (3) a positioning table on which the indicator system under study is mounted and which provides spatial location coordinates for all data points. The test results for both systems are tabulated.
Gorstein, M.↗
A linear combination of modified Bessel functions
A linear combination of modified Bessel functions is defined, discussed briefly, and tabulated. This combination was found to recur in the analysis of various heat transfer problems and in the analysis of the thermal behavior of living tissue when modeled by cylindrical shells.
Shitzer, A.↗
Absolute intensity calibrations of solar K line profiles
Individual K-line profiles from elements of fine structure on the surface of the sun are calibrated absolutely. The continuum calibrations of Labs and Neckel and of Houtgast and Namba are considered, and the average K-profile is scaled to that of White and Suemoto. The ranges of intensities across a high-resolution spectrogram are tabulated for various parts of the line profile. Although the spatially-averaged value for K3 of 4.2% of the continuum corresponds to a brightness temperature of 4155 deg K, minimum and maximum values were 3980 and 4360 K, respectively. Similarly, K2v ranges from 4200 to 4560 K, and K2r from 4180 to 4460 K in small elements about 1 arc sec across.
Pasachoff, J., M.↗
Guidance and navigation requirements for unmanned flyby and swingby missions to the outer planets. Volume 4: High thrust mission, part 2, phase C
The guidance and navigation requirements for a set of impulsive thrust missions involving one or more outer planets or comets. Specific missions considered include two Jupiter entry missions of 800 and 1200 day duration, two multiple swingby missions with the sequences Jupiter-Uranus-Neptune and Jupiter-Saturn-Pluto, and two comets rendezvous missions involving the short period comets P/Tempel 2 and P/Tuttle-Giacobini-Kresak. Results show the relative utility of onboard and Earth-based DSN navigation. The effects of parametric variations in navigation accuracy, measurement rate, and miscellaneous constraints are determined. The utility of a TV type onboard navigation sensor - sighting on planetary satellites and comets - is examined. Velocity corrections required for the nominal and parametrically varied cases are tabulated.
Source record↗
Experiment module concepts study. Volume 2: Experiments and mission operations
The baseline experiment program is concerned with future space experiments and cover the scientific disciplines of astronomy, space physics, space biology, biomedicine and biotechnology, earth applications, materials science, and advanced technology. The experiments within each discipline are grouped into functional program elements according to experiments that support a particular area of research or investigation and experiments that impose similar or related demand on space station support systems. The experiment requirements on module subsystems, experiment operating modes and time profiles, and the role of the astronaut are discussed. Launch and rendezvous with the space station, disposal, and on-orbit operations are delineated. The operational interfaces between module and other system elements are presented and include space station and logistic system interfaces. Preliminary launch and on-orbit environmental criteria and requirements are discussed, and experiment equipment weights by functional program elements are tabulated.
Macdonald, J. M.↗
Space shuttle: Heat transfer rate measurements on Convair booster (B-15B-2) at nominal Mach number of 8
Plotted and tabulated data on heat transfer from a thin-skin thermocouple are presented. The data is representative of the reentry event of the booster alone configuration. The data were generated during wind tunnel tests of the B-15B-2 delta wing booster at Mach 8. Thermocouple measurements are reduced to heat transfer coefficient ratio and the data are presented as plotted variations versus longitudinal, lateral, and vertical local model positions.
Warmbrod, J. D.↗