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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 181 records · Page 10
All sourcesNASA NTRSDOE OSTI
NASA NTRS1982

Energy efficient engine ICLS Nacelle detail design report

The results of the detail design of the Nacelle for the General Electric Energy Efficient Engine (E3) Integrated Core Low Spool (ICLS) test vehicles are presented. A slave nacelle is designed for the ICLS test. Cost and reliability are the important factors considered. The slave nacelle simulates the internal flow lines of the actual Flight Propulsion System (FPS) but has no external fairing. The aerodynamic differences between the ICLS and FPS nacelles are presented, followed by the structural description and analysis of the various nacelle components.

Eskridge, R. R.↗
NASA NTRS1985

Detailed pressure distribution measurements obtained on several configurations of an aspect-ratio-7 variable twist wing

Detailed pressure distribution measurements were made for 11 twist configurations of a unique, multisegmented wing model having an aspect ratio of 7 and a taper ratio of 1. These configurations encompassed span loads ranging from that of an untwisted wing to simple flapped wings both with and without upper-surface spoilers attached. For each of the wing twist configurations, electronic scanning pressure transducers were used to obtain 580 surface pressure measurements over the wing in about 0.1 sec. Integrated pressure distribution measurements compared favorably with force-balance measurements of lift on the model when the model centerbody lift was included. Complete plots and tabulations of the pressure distribution data for each wing twist configuration are provided.

Holbrook, G. T.↗
NASA NTRS1985

A detailed analysis of the erythropoietic control system in the human, squirrel, monkey, rat and mouse

The erythropoiesis modeling performed in support of the Body Fluid and Blood Volume Regulation tasks is described. The mathematical formulation of the species independent model, the solutions to the steady state and dynamic versions of the model, and the individual species specific models for the human, squirrel monkey, rat and mouse are outlined. A detailed sensitivity analysis of the species independent model response to parameter changes and how those responses change from species to species is presented. The species to species response to a series of simulated stresses directly related to blood volume regulation during space flight is analyzed.

Nordheim, A. W.↗
NASA NTRS1984

Detailed studies of the electron lateral distribution in extensive air showers with energies around 10(16) eV

Detailed studies have been performed of the electron lateral distribution in extensive air showers using the Lodz extensive air shower array. The showers were grouped according to their particle densities around 20 m from the core. The grouping was made in very narrow intervals of the densities. For every group of showers and for every distance interval /changing by 5 m/ histograms of the numbers of electron counters discharged have been obtained. The trays of G.M counters were located at following distances from the center of the triggering detectors array: 16 m, 76 m, 117 m, 137 m, 141 m and 147 m.

Dzikowski, T.↗
NASA NTRS1984

Detailed examination of a plasmoid in the distant magnetotail with ISEE 3

Details of an investigation of a lone plasmoid encountered by the ISEE-3 spacecraft in February 1983 are reported. ISEE-3 was then at 217 earth radii distance, in the magnetosheath, and had entered the magnetotail. Intense energetic particle, plasma and magnetic field fluctuations were detected, indicating a large electron flux moving tailward, a suprathermal proton flux, a jump in electron temperature, and inverse signatures of an increasing magnetic field. Closed magnetic field lines were also detected as were IMF field lines around the plasmoid and open field lines connecting the earth with space. The hot particles in the plasmoid are concluded to have been magnetically confined in a boundary one earth radius thick. An earthward directed beam was also detected and was found to balance the tailward flux. The origin and characteristics of the beam were not discerned.

Hones, E. W., Jr.↗
NASA NTRS1984

A detailed X-ray and radio comparison of Kepler's supernova remnant

High-resolution radio images of Kepler's SNR (SNR (SN 1604) at 6 and 21 cm have been obtained using the VLA. The orientation of linear polarization in the SNR implies a substantial nonrandom radial component for the magnetic field of the remnant. Based on a new X-ray picture of the SNR, obtained using the Einstein Observatory, a detailed comparison of the X-ray and radio morphology is carried out. There is a good correlation between rotation measure, obtained from the radio maps, and emission measure, an X-ray-derived quantity in the SNR shell. From the mean electron density value infered from an analysis of X-ray fluxes, a mean radial magnetic field of 14 micro G and a total magnetic field of 70 microG are estimated. The energy density of relativistic electrons in Kepler's SNR in the shell comparable to the energy density in the magnetic field; the relativistic electron-pressure is 2 percent of the thermal gas pressure. The strong correlation between radio emissivity and X-ray emissivity found over the SNR in somewhat large scale can be ascribed to acceleration of thermal electrons at the shock wave and insignificant diffusion of resultant relativistic electrons.

Matsui, Y.↗
NASA NTRS1985

The detailed intensity distribution of the AKR emission cone

The detailed intensity distribution of auroral kilometric radiation (AKR) at frequencies near the spectral peak of 200 kHz and below, over the entire northern hemisphere at large radial distances, is presented based on 3.5 years of IMP 6 data and four years of Hawkeye data. The time-averaged intensity of the AKR emission cone at frequencies from 178 to 100 kHz is found to be nearly uniform. Evidence contradicts a 'hollow cone' structure. The solid angles for the AKR emission cones studied are in good agreement with previously published results, and there is good agreement with previously determined AKR source location. The time-averaged picture of the AKR emission pattern at 178 kHz is representative of the instantaneous AKR emission. Present theories for the generation and propagation of AKR appear insufficient to explain the observed illumination pattern.

Green, J. L.↗
NASA NTRS1986

The near-earth cross-tail current sheet - Detailed ISEE 1 and 2 case studies

Three near geomagnetic tail current sheet crossings of the ISEE 1 and 2 satellites, on April 5, 1979, are examined in detail. All are assoicated with the passage of an interplanetary shock and the region of variable solar wind pressure behind it. The general geometry of field reversing current sheets is discussed, and this geometry is examined for the cases studied, by using the ISEE 1 and 2 coorbiting satellite data sets. A new technique is employed which removes the effects of a variable sheet normal velocity for the first time. This allows us to calculate firm upper bounds on the current sheet thicknesses, and by utilizing certain physically motivated assumptions, determine the most probable actual sheet thicknesses, and inclinations of the field lines within these sheets. Current density profiles derived with this technique show the main cross-tail current sheet to be a structure that is many thermal ion-gyroradii thick and which is sometimes imbedded in a region that is three or more times thicker and contains much smaller current densities. These profiles also exhibit a considerable amount of fine structure in the sheet which appears as narrow peaks in the current density distributions. Possible explanations for these structures, and for the overall sheet structure itself, are examined.

Mccomas, D. J.↗
NASA NTRS1986

Detailed three-dimensional isentropic analysis using an objective cross-sectional approach

An approach is presented which is designed to give detailed, computationally-efficient meteorological objective analyses over data-rich regions, with results independent of numerical model influences. Observed station data and interstation gradients are used to interpolate pressure, wind, and moisture information from vertical cross-sections onto isentropci surfaces by means of cubic polynomials. Three-dimensional grid-point analyses of mass and moisture are obtained by first constructing a series of nearly parallel vertical cross sections over a specified area, and then filling in the space between adjacent vertical analyses by employing a second set of nearly orthogonal cross sections. Gradients obtained from the mass analyses are then combined with observed wind data to obtain thermally-consistent observed wind analyses. It is concluded that the resulting analyses are useful for preserving significnat horizontal and vertical gradients, such as those associated with jet-streak systems. Examples are given which verify the applicability of this analysis technique to radiosonde data.

Petersen, R. A.↗
NASA NTRS1987

Detailed flow surveys of turning vanes designed for a 0.1-scale model of NASA Lewis Research Center's proposed altitude wind tunnel

Detailed flow surveys downstream of the corner turning vanes and downstream of the fan inlet guide vanes have been obtained in a 0.1-scale model of the NASA Lewis Research Center's proposed Altitude Wind Tunnel. Two turning vane designs were evaluated in both corners 1 and 2 (the corners between the test section and the drive fan). Vane A was a controlled-diffusion airfoil and vane B was a circular-arc airfoil. At given flows the turning vane wakes were surveyed to determine the vane pressure losses. For both corners the vane A turning vane configuration gave lower losses than the vane B configuration in the regions where the flow regime should be representative of two-dimensional flow. For both vane sets the vane loss coefficient increased rapidly near the walls.

Moore, Royce D.↗
NASA NTRS1986

Detailed near-wake flowfield surveys with comparison to an Euler method of an aspect ratio 4 rectangular wing

An experimental investigation of the flowfield in the near-wake of an aspect ratio 4 rectangular wing was conducted, providing a complete detailed set of data for use in the validation of computational methods. An angle of attack of 8 degrees and two Reynolds numbers 530,000 and 391,000 were investigated using pitot and six-hole probes. In addition, two types of flow visualization were employed. The data presented includes contours of total pressure, mean velocity, flow angularity, and vorticity distribution data at five chordwise stations of the near-wake ranging from 0.167 to 5.00 chord lengths aft of the trailing edge. The experimental results were compared to the predicted results of a 2-D Euler numerical method. The results predicted by an Euler method failed to accurately define the flowfield. Tangential velocities remained relatively constant over the range of X/C considered though increased in angle of attack and Reynolds number did bring about corresponding increases. Axial velocities also increased with angle of attack and Reynolds number but showed greater sensitivity to increases in X/C. Graphic displays and contours of the total pressure data indicate that roll-up of the wing tip vortex is essentially complete one and one half chords downstream of the trailing edge.

Klinge, M. D.↗
NASA NTRS1987

A detailed description of the uncertainty analysis for High Area Ratio Rocket Nozzle tests at the NASA Lewis Research Center

A preliminary uncertainty analysis has been performed for the High Area Ratio Rocket Nozzle test program which took place at the altitude test capsule of the Rocket Engine Test Facility at the NASA Lewis Research Center. Results from the study establish the uncertainty of measured and calculated parameters required for the calculation of rocket engine specific impulse. A generalized description of the uncertainty methodology used is provided. Specific equations and a detailed description of the analysis are presented. Verification of the uncertainty analysis model was performed by comparison with results from the experimental program's data reduction code. Final results include an uncertainty for specific impulse of 1.30 percent. The largest contributors to this uncertainty were calibration errors from the test capsule pressure and thrust measurement devices.

Kenneth J. Davidian↗
NASA NTRS1985

The SIFT hardware/software systems. Volume 1: A detailed description

This report contains a detailed description of the software implemented fault-tolerant computer's operating system and hardware subsystems. The Software Implemented Fault-Tolerant (SIFT) computer system was developed as an experimental vehicle for fault-tolerant systems research. The SIFT effort began with broad, in-depth studies stating the reliability and processing requirements for digital computers which would, in the aircraft of the 1990's, control flight-critical functions.

Palumbo, Daniel L.↗
NASA NTRS1987

Detailed mechanism of benzene oxidation

A detailed quantitative mechanism for the oxidation of benzene in both argon and nitrogen diluted systems is presented. Computed ignition delay time for argon diluted mixtures are in satisfactory agreement with experimental results for a wide range of initial conditions. An experimental temperature versus time profile for a nitrogen diluted oxidation was accurately matched and several concentration profiles were matched qualitatively. Application of sensitivity analysis has given approximate rate constant expressions for the two dominant heat release reactions, the oxidation of C6H5 and C5H5 radicals by molecular oxygen.

Bittker, David A.↗
NASA NTRS1988

Detailed mechanism of toluene oxidation and comparison with benzene

A detailed mechanism for the oxidation of toluene in both argon and nitrogen dilutents is presented. The mechanism was used to compute experimentally ignition delay times for shock-heated toluene-oxygen-argon mixtures with resonably good success over a wide range of initial temperatures and pressures. Attempts to compute experimentally measured concentration profiles for toluene oxidation in a turbulent reactor were partially successful. An extensive sensitivity analysis was performed to determine the reactions which control the ignition process and the rates of formation and destruction of various species. The most important step was found to be the reaction of toluene with molecular oxygen, followed by the reactions of hydroperoxyl and atomic oxygen with benzyl radicals. These findings contrast with the benzene oxidation, where the benzene-molecular oxygen reaction is quite unimportant and the reaction of phenyl with molecular oxygen dominates. In the toluene mechanism the corresponding reaction of benzyl radicals with oxygen is unimportant. Two reactions which are important in the oxidation of benzene also influence the oxidation of toluene for several conditions. These are the oxidations of phenyl and cyclopentadienyl radicals by molecular oxygen. The mechanism presented successfully computes the decrease of toluene concentration with time in the nitrogen diluted turbulent reactor. This fact, in addition to the good prediction of ignition delay times, shows that this mechanism can be used for modeling the ignition and combustion process in practical, well-mixed combustion systems.

Bittker, David A.↗
NASA NTRS1987

A detailed description of the uncertainty analysis for high area ratio rocket nozzle tests at the NASA Lewis Research Center

A preliminary uncertainty analysis was performed for the High Area Ratio Rocket Nozzle test program which took place at the altitude test capsule of the Rocket Engine Test Facility at the NASA Lewis Research Center. Results from the study establish the uncertainty of measured and calculated parameters required for the calculation of rocket engine specific impulse. A generalized description of the uncertainty methodology used is provided. Specific equations and a detailed description of the analysis is presented. Verification of the uncertainty analysis model was performed by comparison with results from the experimental program's data reduction code. Final results include an uncertainty for specific impulse of 1.30 percent. The largest contributors to this uncertainty were calibration errors from the test capsule pressure and thrust measurement devices.

Davidian, Kenneth J.↗
NASA NTRS1985

PC-based Multiple Information System Interface (PC/MISI) detailed design and implementation plan

The design plan for the personal computer multiple information system interface (PC/MISI) project is discussed. The document is intended to be used as a blueprint for the implementation of the system. Each component is described in the detail necessary to allow programmers to implement the system. A description of the system data flow and system file structures is given.

Dominick, Wayne D.↗