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At least 919 records · Page 51
All sourcesNASA NTRSDOE OSTI
NASA NTRS1978

Transport properties in the Jovian atmosphere

Transport properties in a Jupiter-like atmosphere (89 mol % hydrogen and 11 mol % helium) are obtained by using the method of the kinetic theory of gases. The transport collision integrals are calculated by fitting various two-body semiempirical interaction potentials for which the collision integrals are tabulated to ab initio quantum mechanical calculations of the two-body interactions. The collision integrals are used to calculate the binary diffusion coefficients, viscosity, and 'total' thermal conductivity of the pure gases and the gas mixtures at 1-atm pressure from 1000 K to 25,000 K.

Biolsi, L.↗
NASA NTRS1978

Collisional excitation of interstellar molecules - H2

Cross sections for the important rotational transitions in molecular hydrogen collisions are presented for rotational levels to j = 11 and energies to 20,000 K. These have been obtained from extensive theoretical calculations. The resulting cross sections are fitted to a simple polynomial in the energy, and the coefficients are tabulated for easy utilization.

Green, S.↗
NASA NTRS1978

Some effects of ablation on transport properties in the Jovian atmosphere

In this paper the transport properties at the inner and outer boundary for mixing between ablation products and a Jovian-like atmosphere are calculated. The dominant species at these boundaries are C, H, O, He, H+, and e. Accurate potential energy curves are obtained for the fifteen possible two-body interactions among these species by fitting good semiempirical potentials for which transport collision cross sections have been tabulated to accurate experimental and theoretical information. Results are obtained for the viscosity and translational thermal conductivity of the pure species and the binary diffusion coefficients from 1000 K to 25,000 K. In addition, the mixture translational thermal conductivity and viscosity are calculated at the inner and outer mixing boundaries. This information is required for calculating flowfield properties and surface heating. The most important conclusion is that the translational thermal conductivity is substantially lower at the inner mixing boundary than it is at the outer mixing boundary.

Biolsi, L.↗
NASA NTRS1978

Interstellar absorption lines in the spectrum of Zeta Puppis

The far-UV spectrum of Zeta Pup is surveyed as obtained from scans by Copernicus satellite detectors. Equivalent widths are tabulated for 147 lines from 35 different ions or isotopes of 19 elements in the direction of Zeta Pup. In addition, 52 unidentified absorption lines are listed whose narrow widths indicate an interstellar origin. An attempt is made to report on the relative velocities of the lines, curves of growth and column densities, and interstellar abundances. Suggestions are made for future investigations. Apparently, it is found that: (1) O, P, S, Cl, and Zn are within a factor of 2 of their solar abundances toward Zeta Pup; (2) Mg, Al, Si, Cr, Mn, Fe, Ni, and Cu are depleted by factors of 4 or more; and (3) the depletion generally increases with increasing condensation temperature.

Morton, D. C.↗
NASA NTRS1978

Stellar model chromospheres. VIII - 70 Ophiuchi A /K0 V/ and Epsilon Eridani /K2 V/

Model atmospheres for the late-type active-chromosphere dwarf stars 70 Oph A and Epsilon Eri are computed from high-resolution Ca II K line profiles as well as Mg II h and k line fluxes. A method is used which determines a plane-parallel homogeneous hydrostatic-equilibrium model of the upper photosphere and chromosphere which differs from theoretical models by lacking the constraint of radiative equilibrium (RE). The determinations of surface gravities, metallicities, and effective temperatures are discussed, and the computational methods, model atoms, atomic data, and observations are described. Temperature distributions for the two stars are plotted and compared with RE models for the adopted effective temperatures and gravities. The previously investigated T min/T eff vs. T eff relation is extended to Epsilon Eri and 70 Oph A, observed and computed Ca II K and Mg II h and k integrated emission fluxes are compared, and full tabulations are given for the proposed models. It is suggested that if less than half the observed Mg II flux for the two stars is lost in noise, the difference between an active-chromosphere star and a quiet-chromosphere star lies in the lower-chromospheric temperature gradient.

Kelch, W. L.↗
NASA NTRS1978

A comparison of synthetic and measured solar continuum intensities and limb darkening coefficients

The paper compares recent center-limb studies of optical and IR continuum intensities (over the wavelength range 0.3-2.4 microns, with the data tabulated in the form of second- and fifth-order polynomial fits to empirical limb darkening curves) by Pierce and Slaughter (1977) and by Pierce et al. (1977) with predictions based on several current photospheric thermal structure models, using calibrated specific intensity measurements by Labs and Neckel (1968, 1970) to set an absolute temperature scale. The thermal structure in best quantitative agreement with the measurements of Pierce and Slaughter and Pierce et al. is the semiempirical model of Vernazza, Avrett and Loeser (1976). The temperatures in this model must be scaled upward, however, by a factor of 1.015 plus or minus 0.0005 to be consistent with the Labs and Neckel absolute calibration of continuum high points in the 0.40-0.65 micron region.

Ayres, T. R.↗
NASA NTRS1978

Transport properties of monatomic carbon

Transport collision integrals for each of the 18 molecular C2 states that dissociate into ground state carbon atoms are presented. The integrals are obtained by fitting two-body semiempirical interaction potentials, for which the collision integrals are tabulated, to experimental and/or accurate theoretical calculations for each of these states. The collision integrals are applied to calculate the diffusion coefficient, viscosity, and translational contribution to the thermal conductivity of monatomic carbon at 1-atm pressure from 1000 K to 25,000 K. Because of ablation injection, monatomic carbon is an important flow field constituent of ablative flow during planetary entry, and knowledge of the transport properties for carbon species is required for calculating the flow field properties and surface heating.

Biolsi, L.↗
NASA NTRS1978

Extreme ultraviolet spectrum of a hot interstellar plasma

The EUV (100-1000 A) spectrum of an optically thin plasma over the temperature range 100,000-10 million K is calculated, and the effects of free-free, free-bound, and two-photon continuum radiation are considered. The resulting spectra are presented in graphical form, with a separate tabulation of intensities for the emission lines. Results in the 100-200 A region are compared with those of other workers, and the major sources of uncertainty in this type of calculation are discussed. The applicability of the results to EUV observations of the interstellar medium are also mentioned.

Stern, R.↗
NASA NTRS1978

Characterization of the non axial thrust generated by large solid propellant rocket motors in three axis stabilized ascent

Nonaxial thrusts produced by solid rocket motors during three-axis stabilized attitude control have been determined from ascent experience on twenty three Burner II, Burner IIA and Block 5D-1 upper stage vehicles. A data base representing four different rocket motor designs (three spherical and one extended spherical) totaling twenty five three-axis stabilized firings is generated. Solid rocket motor time-varying resultant and lateral side force vector magnitudes, directions and total impulses, and roll torque couple magnitudes, directions, and total impulses are tabulated in the appendix. Population means and three sigma deviations are plotted. Existing applicable ground test side force and roll torque magnitudes and total impulses are evaluated and compared to the above experience data base. Within the spherical motor population, the selected AEDC ground test data consistently underestimated experienced motor side forces, roll torques and total impulses. Within the extended spherical motor population, the selected AEDC test data predicted experienced motor side forces, roll torques, and total impulses, with surprising accuracy considering the very small size of the test and experience populations.

Kosmann, W. J.↗
NASA NTRS1978

Theoretical intensity ratios for the UV lines of Mg VII, Si IX and S XI

Energy levels, oscillator strengths, and electron collision strengths have been computed for the configurations 2s2 2p2, 2s 2p3, 2p4 of Mg VII, Si IX, and S XI. Level populations for the ground configuration and theoretical intensity ratios for the UV lines are tabulated for electron densities and temperatures appropriate to the solar atmosphere. The identification of the Mg VII, Si IX, and S XI UV lines is discussed.

Mason, H. E.↗
NASA NTRS1980

Collector performance at various air-channel depths

Report describes evaluation of solar collector efficiency which was measured at airflow channel depths of 3, 2, 1, and 1/2 inches in solar simulator. Data were also recorded on absorber surface temperature, inlet and outlet temperatures, airflow and insolation rates, collector differential pressure and windspeed, for result tabulation and plotting.

Source record↗
NASA NTRS1978

Anthropometry

Data on body-size measurement are presented to aid in spacecraft design. Tabulated dimensional anthropometric data on 59 variables for 12 selected populations are given. The variables chosen were those judged most relevant to the manned space program. A glossary of anatomical and anthropometric terms is included. Selected body dimensions of males and females from the potential astronaut population projected to the 1980-1990 time frame are given. Illustrations of drawing-board manikins based on those anticipated body sizes are included.

Mcconville, J. T.↗
NASA NTRS1978

The M-15-aircraft (samolot M-15)

The M-15 is an all-metal, semimonocoque, twin-tail-boom sesquiplane aircraft designed exclusively for agricultural support operations involving slow low-level flight. It is powered by a single Al-25 bypass turbojet engine used in the Yak-40 aircraft. Tanks for spraying chemicals are mounted between the lower and upper wings. Dimensions, weights, and performance data are tabulated.

Leiiecki, R.↗
NASA NTRS1979

Exploratory investigation of the effect of porous surfaces on hypersonic turbulent boundary layers

Four different test surfaces were studied to determine the effect of porous walls on the characteristics of a hypersonic turbulent flat-plate boundary layer. The investigation was an attempt to decrease the surface shear of the boundary layer by transmitting fluctuating pressure energy through the wall and absorbing it in a cavity beneath the wall. Pitot surveys were made at two locations, schlieren photographs of the boundary layer were taken, and hot-wire measurements in the flow above the boundary layer were made to determine whether the surfaces affected the turbulent boundary layer. Neither an increase nor a decrease in surface shear or boundary-layer growth was detected. Tabulations of the pitot data are included.

Watson, R. D.↗
NASA NTRS1978

Initial evaluation tests of Eagle-Picher Industries 9.0 ampere-hour nickel-cadmium spacecraft cells for the heat capacity mapping mission satellite and the stratospheric aerosol and gas experiment satellite

The results of tests to insure that all cells put into the life cycle program are of high quality are reported. The tests consisted of the following: phenolptalein leak tests, internal short test, charge efficiency test, and overcharge tests. The results of tests for 10 cells are tabulated.

Harkness, J. D.↗
NASA NTRS1979

Launch vehicle effluent measurements during the August 20, 1977, Titan 3 launch at Air Force Eastern Test Range

Airborne effluent measurements within the launch cloud and visible and infrared measurements of cloud physical behavior are discussed. Airborne effluent measurements include concentrations of HCl, Cl2, NO, NOX, and particulates as a function of time during each sampling pass through the exhaust cloud. The particle size distribution was measured for each pass through the cloud. Mass concentration as a function of particle diameter was measured over the size range of 0.05- to 25 micron diameter, and particle number density was measured as a function of diameter over a size range of 0.5 to 7.5 micron. Effluent concentrations in the cloud ranged from about 30 ppm several minutes after launch to about 1 to 2 ppm at 100 minutes. Maximum Cl2 concentrations were about 40 to 55 ppb and by 20 minutes were less than 1.0 ppb. A tabulated listing of the airborne data is given in the appendix. Usable cloud imaging data were limited to the first 16 minutes after launch.

Woods, D. C.↗
NASA NTRS1979

Acoustic scattering by circular cylinders of various aspect ratios

The effects of acoustic scattering on the useful frequency range of pressure gradient microphones were investigated experimentally between ka values of 0.407 and 4.232 using two circular cylindrical models (L/D = 0.5 and 0.25) having a 25 cm outside diameter. Small condenser microphones, attached to preamplifiers by flexible connectors, were installed from inside the cylindrical bodies, and flush mounted on the exterior surface of the cylinders. A 38 cm diameter woofer in a large speaker enclosure was used as the sound source. Surface pressure augmentation and phase differences were computed from measured data for various sound wave incidence angles. Results are graphically compared with theoretical predictions supplied by NASA for ka = 0.407, 2.288, and 4.232. All other results are tabulated in the appendices. With minor exceptions, the experimentally determined pressure augmentations agreed within 0.75 dB with theoretical predictions. The agreement for relative phase angles was within 5 percent without any exceptions. Scattering parameter variations with ka and L/D ratio, as computed from experimental data, are also presented.

Maciulaitis, A.↗
NASA NTRS1979

Results of transonic tests in the NASA/MSFC 14-inch trisonic wind tunnel on a 0.004-scale model (74-OTS) space shuttle launch vehicle (FA25)

The primary objective of the test was to determine the aerodynamic increments due to the attach structure. Secondary objectives were to determine the effects of: (1) orbiter nose mold line changes; (2) wire bundle fairings on data measurements; and (3) flow angularity. The scale model was tested over the Mach range from 0.60 to 1.25 at angles of attack and sideslip from -8 to +8 deg. The total pressure was 22 psia for all runs. Six-component orbiter data were obtained from a balance in the orbiter which was sting supported. The external tank was attached to the solid rocket booster, each of which was sting supported. An alternate two sting/two balance arrangement was also tested with a single sting and balance in the external tank measuring combined ET/SRB aero data replacing the two stings in the SRB's. Two runs were also made at Mach number 4.96 with the two SRB's removed. The aerodynamic coefficients obtained are tabulated as a function of angle of attack or sideslip for each Mach number value.

Lundy, T. E.↗