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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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At least 271 records · Page 15
All sourcesNASA NTRSDOE OSTI
NASA NTRS1982

Improvement of Rocket Engine Plume Analysis Techniques

A nozzle plume flow field code was developed. The RAMP code which was chosen as the basic code is of modular construction and has the following capabilities: two phase with two phase transonic solution; a two phase, reacting gas (chemical equilibrium reaction kinetics), supersonic inviscid nozzle/plume solution; and is operational for inviscid solutions at both high and low altitudes. The following capabilities were added to the code: a direct interface with JANNAF SPF code; shock capturing finite difference numerical operator; two phase, equilibrium/frozen, boundary layer analysis; a variable oxidizer to fuel ratio transonic solution; an improved two phase transonic solution; and a two phase real gas semiempirical nozzle boundary layer expansion.

Smith, S. D.↗
NASA NTRS1982

Thermodynamic and transport combustion properties of hydrocarbons with air. Part 1: Properties in SI units

Thermodynamic and transport combustion properties were calculated for a wide range of conditions for the reaction of hydrocarbons with air. Three hydrogen-carbon atom ratios (H/C = 1.7, 2.0, 2.1) were selected to represent the range of aircraft fuels. For each of these H/C ratios, combustion properties were calculated for the following conditions: Equivalence ratio: 0, 0.25, 0.5, 0.75, 1.0, 1.25 Water - dry air mass ratio: 0, 0.03 Pressure, kPa: 1.01325, 10.1325, 101.325, 1013.25, 5066.25 (or in atm: 0.01, 0.1, 1, 10, 50) Temperature, K: every 10 degrees from 200 to 900 K; every 50 degrees from 900 to 3000 K Temperature, R: every 20 degrees from 360 to 1600 R; very 100 degrees from 1600 to 5400 R. The properties presented are composition, density, molecular weight, enthalphy, entropy, specific heat at constant pressure, volume derivatives, isentropic exponent, velocity of sound, viscosity, thermal conductivity, and Prandtl number. Property tables are based on composites that were calculated by assuming both: (1) chemical equilibrium (for both homogeneous and heterogeneous phases) and (2) constant compositions for all temperatures. Properties in SI units are presented in this report for the Kelvin temperature schedules.

Gordon, S.↗
NASA NTRS1981

Models of the earth's core

Combined inferences from seismology, high-pressure experiment and theory, geomagnetism, fluid dynamics, and current views of terrestrial planetary evolution lead to models of the earth's core with five basic properties. These are that core formation was contemporaneous with earth accretion; the core is not in chemical equilibrium with the mantle; the outer core is a fluid iron alloy containing significant quantities of lighter elements and is probably almost adiabatic and compositionally uniform; the more iron-rich inner solid core is a consequence of partial freezing of the outer core, and the energy release from this process sustains the earth's magnetic field; and the thermodynamic properties of the core are well constrained by the application of liquid-state theory to seismic and labroatory data.

Stevenson, D. J.↗
NASA NTRS1981

The ionospheric peak on the Venus dayside

The behavior of the ionospheric peak on the dayside of Venus is described and interpreted by combining radio occultation measurements with theoretical calculations. The theoretical models are shown to be able to reproduce the measured electron densities very accurately when careful consideration is given to such parameters as the level of solar activity, the electron temperature, and the neutral density. What is more, the models are able to provide a check on the accuracy of neutral atmospheric models in the vicinity of 140 km. Chemical equilibrium is assumed for the calculation of ion and electron densities. A table giving Pioneer Venus radio occultation measurements of the Venus dayside ionosphere is included.

Cravens, T. E.↗
NASA NTRS1982

Galileo probe forebody flowfield predictions during Jupiter entry

This paper presents forebody flowfield solutions for Jupiter entry conditions where the ablation injection rate is coupled with the surface heating rate. The calculations are made with a time-dependent viscous-shock-layer analysis where the flow is assumed to be in chemical equilibrium. The results obtained demonstrate how variations in various properties influence the calculations and how recent modifications in probe forebody heatshield design influence the heating and mass-loss conditions for Jupiter entry. The heatshield mass-loss rates are shown to decrease when the new radiative and thermodynamic property values are used as well as when the nose bluntness is reduced. Also, the inclusion of a finite surface reflectivity reduces the mass loss whereas spallation increases the mass loss by about 6 percent. Finally, the heating, mass-loss, and flowfield structure characteristics are described for a 335-kg probe as it enters the atmosphere of Jupiter.

Moss, J. N.↗
NASA NTRS1982

Chemistry and phase relations of VLT volcanic glasses from Apollo 14 and Apollo 17

The VLT (very low titanium) volcanic glasses from Apollo 14 and Apollo 17 have been analyzed for the major elements and trace Ni. These glasses display compositional trends that may not result entirely from olivine fractionation. The phase relations have been determined experimentally. Olivine is the liquidus phase in the pressure interval from 0 to about 18 kbar. Pigeonite is the liquidus phase from about 18 kbar to 22 kbar or more. If these VLT volcanic glasses are samples of primary melts that had been in chemical equilibrium with olivine and low-Ca pyroxene in their source regions, then these liquids were derived from depths of 360-380 km within the moon.

Chen, H.-K.↗
NASA NTRS1983

Real gas flow fields about three dimensional configurations

Real gas, inviscid supersonic flow fields over a three-dimensional configuration are determined using a factored implicit algorithm. Air in chemical equilibrium is considered and its local thermodynamic properties are computed by an equilibrium composition method. Numerical solutions are presented for both real and ideal gases at three different Mach numbers and at two different altitudes. Selected results are illustrated by contour plots and are also tabulated for future reference. Results obtained compare well with existing tabulated numerical solutions and hence validate the solution technique.

Balakrishnan, A.↗
NASA NTRS1983

Identification of deuterium ions in the ionosphere of Venus

The dominant mass two ion in the ionosphere of Venus is identified as D(+) through analysis of the height variation of (mass two ion)/(H(+)) measured in the chemical equilibrium region by the ion mass spectrometer on the Pioneer Venus Orbiter. This result leads to (D)/(H) = (2.2 + or - 0.6) x 10 to the -2 at the turbopause, which agrees with the ratio measured in the lower atmosphere by the large probe mass spectrometer. The 100-fold deuterium enrichment supports previous suggestions that Venus has lost at least 0.3 percent of a terrestrial ocean.

Hartle, R. E.↗
NASA NTRS1984

Ionospheric chemistry of NO(+)

An investigation is described of the behavior of NO(+) in the daytime F region, with basic ion concentration measurements from the Atmosphere Explorer C satellite. The data set was acquired along select orbits at low latitudes and exhibits substantial variations in the NO(+) concentration, both along and between nearby orbits. An excellent consistency is demonstrated between these observations and current chemical equilibrium theory, in contrast to differences that have been reported for the related N2(+) ion. Large variations in the concurrently observed electron temperature permit a relevant comparison between different laboratory determinations of the dissociative recombination rate coefficient. Contributions to the NO(+) production from several secondary sources are also evaluated. Results strengthen the basis for the current theoretical ionospheric chemistry of NO(+) and establish important constraints on resolution of the difficulties with N2(+).

Breig, E. L.↗
NASA NTRS1984

Flowfield computation of an aerobrake orbital transfer vehicle

Viscous real gas and ideal gas supersonic flowfields over the forebody of a aeroassisted orbital transfer vehicle are determined using a unsteady factored implicit algorithm. Air in chemical equilibrium is considered and its local thermodynamic properties are computed by an equilibrium composition method. Numerical solutions are obtained for both real and ideal gases at a Mach number of 30 and at angles of attack up to 20 degrees. Shock stand-off distances and surface pressure distributions are presented for the gas models with and without viscous effects. For the freestream conditions considered, viscous effects dominate the flow.

Balakrishnan, A.↗
NASA NTRS1985

Prediction of Combustion Gas Deposit Compositions

Demonstrated procedure used to predict accurately chemical compositions of complicated deposit mixtures. NASA Lewis Research Center's Computer Program for Calculation of Complex Chemical Equilibrium Compositions (CEC) used in conjunction with Computer Program for Calculation of Ideal Gas Thermodynamic Data (PAC) and resulting Thermodynamic Data Base (THDATA) to predict deposit compositions from metal or mineral-seeded combustion processes.

Kohl, F. J.↗
NASA NTRS1985

Liquid rocket combustor computer code development

The Advanced Rocket Injector/Combustor Code (ARICC) that has been developed to model the complete chemical/fluid/thermal processes occurring inside rocket combustion chambers are highlighted. The code, derived from the CONCHAS-SPRAY code originally developed at Los Alamos National Laboratory incorporates powerful features such as the ability to model complex injector combustion chamber geometries, Lagrangian tracking of droplets, full chemical equilibrium and kinetic reactions for multiple species, a fractional volume of fluid (VOF) description of liquid jet injection in addition to the gaseous phase fluid dynamics, and turbulent mass, energy, and momentum transport. Atomization and droplet dynamic models from earlier generation codes are transplated into the present code. Currently, ARICC is specialized for liquid oxygen/hydrogen propellants, although other fuel/oxidizer pairs can be easily substituted.

Liang, P. Y.↗
NASA NTRS1985

A model for the CI (609 micron) emission of Orion

A numerical model energy balance and chemical equilibrium in the photodissociation regions at the edge of molecular clouds is presented. The model is used to calculate the emergent intensities of the following fine-structure lines: OI (at 63, 145 microns); CI (at 609, 370 microns); C II (at 158 microns); and the low-lying rotational transitions of CO. It is shown that column densities in the range 2 x 10 to the 17th to 2 x 10 to the 18th per sq cm can be obtained for the C(+)/C/CO transition region at the edges of molecular clouds. The difference in the column densities is attributed to changes in the charge exchange reactions of C(+) with SiO and S, and to the process of carbon self-healing. It is found that the calculations are in good agreement with the observed conditions in the photodissociation regions behind Orion (1) C Ori, and near the surface of OMC 1.

Tielens, A. G. G. M.↗
NASA NTRS1986

Theoretical and experimental investigation of the destruction of graphites in a flow of dissociated air

A method is presented for calculating the heating and erosion of blunt bodies made of graphite in a high-enthalpy flow of dissociated air, assuming chemical equilibrium on the surface and taking account of the thermal effects of combustion and sublimation of graphite. The analysis involves the use of a finite difference scheme to solve an equation of unsteady heat conduction. Attention is given to the equilibrium vaporization of C, C2 and C3 molecules. The calculations agree well with experimental data for a wide range of temperatures and stagnation pressures.

Bovina, T. A.↗
NASA NTRS1986

Three-dimensional AOTV flowfields in chemical nonequilibrium

A technique for upwind differencing of the three-dimensional species continuity equations is presented which permits computation of steady flows in chemical equilibrium and nonequilibrium. The capabilities and shortcomings of the present approach for equilibrium and nonequilibrium flows is discussed. Modifications now being investigated to improve computational time are outlined.

Gnoffo, P. A.↗
NASA NTRS1986

The gas composition of Jupiter derived from 5 micron airborne spectroscopic observations

It is pointed out that Jupiter's 5-micron spectrum is a very diagnostic observational tool to probe the troposphere of this giant planet. A report is presented of abundance analyses of NH3, PH3, CH4, CH3D, CO, and GeH4 in the 1- to 6-bar pressure range in Jupiter's troposphere. All the considered molecules have been previously detected in ground-based, airborne, and spacecraft observations of Jupiter. The contribution made by the present study is related to a self-consistent simultaneous determination of the abundances of all of these molecules at the same physical level in Jupiter's atmosphere using one high spectral resolution dataset and a radiative transfer model. It is found that most abundances deviate significantly from expectations based upon an atmospheric model assuming solar composition and chemical equilibrium. The D/H ratio in Jupiter is comparable to that measured in the interstellar medium.

Bjoraker, G. L.↗
NASA NTRS1986

The parental magma of the Nakhla achondrite - Ultrabasic volcanism on the shergottite parent body

An examination of chemical and mineral chemical data available for the cumulate and the intercumulus magma of the Nakhla meteorite is presented. The composition of the intercumulus magma, calculated by mass balance, is found to be ultrabasic (SiO2 is less than 45 percent), and the magma is enriched in incompatible elements (La/Lu=6 x Cl). The cumulus augite and intercumulus magma are in chemical equilibrium, implying that the intercumulus magma is a sample of Nakhla's parental magma. The possibility of Nakhla's Martian origin is discussed.

Treiman, A. H.↗
NASA NTRS1987

Navier-Stokes simulation of a hypersonic generic wing/fuselage

An unsteady thin-layer Navier-Stokes code is used to calculate a generic wing/fuselage configuration at a Mach number of 25 and freestream conditions corresponding to an altitude of 220,000 feet. Calculations were performed with the assumptions of a perfect gas and with chemical equilibrium, and the boundary layer was assumed to be turbulent and to have a surface temperature prescribed at 1255 K. Results for the two different gas assumptions were compared in terms of distributions of pressure, density, temperature, Mach number, ratio of specific heat, and heat transfer. Numerical problems arising in the calculations were identified.

Wai, John C.↗