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  • 1
    Publication Date: 2005-11-27
    Description: Electron density and signal attenuation data from RAM C hypersonic reentries and theoretical calculations
    Keywords: PHYSICS, PLASMA
    Type: THE ENTRY PLASMA SHEATH AND ITS EFFECTS ON SPACE VEHICLE ELECTROMAGNETIC SYSTEMS, VOL. 1 1970; P 277-303
    Format: text
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  • 2
    Publication Date: 2011-08-16
    Description: Electron density profiles which include the effect of an ablated sodium impurity were computed for the boundary layer on a blunt-nosed body re-entering the atmosphere at 7.62 km/sec. Profiles are computed from the nose to a distance of four diameters along the RAM C-payload. A finite-difference, laminar, nonequilibrium chemistry boundary-layer program was used. Comparison of theory with S-band diagnostic antenna results, electron concentration deduced from X- and C-band attenuation data, and Langmuir probe data at several different aft body locations show that agreement is good at high altitude. At the lower altitudes there is disagreement between theory and S-band antenna data where the apparent discrepancy is attributed to the three-body recombination rate constant used for deionization of sodium coupled with the effect of angle of attack.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 12; June 197
    Format: text
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  • 3
    Publication Date: 2019-05-21
    Description: Equilibrium composition and thermodynamic properties of cyanogen-oxygen combustion products
    Keywords: PHYSICS, SOLID-STATE
    Type: NASA-TN-D-2422
    Format: application/pdf
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  • 4
    Publication Date: 2019-06-28
    Description: An anaytical study of hydrogen air kinetics was performed. Calculations were made over a range of pressure from 0.2 to 4.0 atm, temperatures from 850 to 2000 K, and mixture equivalence ratios from 0.2 to 2.0. The finite rate chemistry model included 60 reactions in 20 species of the H2-O2-N2 system. The calculations also included an assessment of how small amounts of the chemicals H2O, NOx, H2O2, and O3 in the initial mixture affect ignition and reaction times, and how the variation of the third body efficiency of H2O relative of N2 in certain key reactions may affect reaction time. The results indicate that for mixture equivalence ratios between 0.5 and 1.7, ignition times are nearly constant; however, the presence of H2O and NO can have significant effects on ignition times, depending on the mixture temperature. Reaction time is dominantly influenced by pressure but is nearly independent of initial temperature, equivalence ratio, and the addition of chemicals. Effects of kinetics on reaction at supersonic combustor conditions are discussed.
    Keywords: INORGANIC AND PHYSICAL CHEMISTRY
    Type: NASA-TP-1856 , L-14379
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  • 5
    Publication Date: 2019-06-27
    Description: New calculations of boundary-layer electron concentration profiles for entry of a blunt-nosed slender body into the earth's atmosphere are compared with previous calculations in which ambipolar diffusion was neglected. The old and new results agree in those flight regimes where ambipolar diffusion is unimportant, but large differences are noted in both peak electron concentration and profile shape at the higher altitudes, where diffusion effects are greatest. The new results are also compared with flight-measured profiles and with calculated profiles for a viscous-shock-layer theory which was recently reported in the literature. The boundary-layer results and the data agree in most respects. Differences which occur between predicted results and the data in the outer parts of the profile are discussed in terms of the effects of aerodynamic heating of the probes.
    Keywords: PHYSICS, PLASMA
    Type: NASA-TN-D-7332
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  • 6
    Publication Date: 2019-06-27
    Description: Calculation of electron concentration for blunt nose at orbital speeds by use of pure air nonequilibrium chemistry throughout flow field and for same flow field with alkali contaminants
    Keywords: PHYSICS, PLASMA
    Type: NASA-TN-D-6294 , L-6705
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  • 7
    Publication Date: 2019-06-27
    Description: The capabilities of a computer program are explored, and computed results are compared with data. The comparisons are restricted to two-dimensional flows. Subsonic and supersonic flows, ducted and nonducted, reacting and nonreacting, are considered. An evaluation of models used for turbulence and chemical reaction was included. Constants in the dissipation rate of turbulent kinetic energy, turbulence model, which produces mixing in good agreement with data, are the same for all calculations. Experimental data are reported for coaxial injection at matched pressure (1 atm or 101.3 kPa) of a cold, Mach 2, hydrogen jet into a hot, Mach 2, vitiated airstream. Profiles of pitot pressure and gas composition obtained from water cooled probes are reported and compared with theoretical results.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TP-1169
    Format: application/pdf
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  • 8
    Publication Date: 2019-06-27
    Description: A correlation of available self ignition data for supersonic hydrogen-air mixtures in configurations representative of scramjet combustors was made. The correlation was examined in light of simplified ignition-limit models. The data and model included cases of injection from transverse fuel jets on walls, transverse jets behind swept and unswept steps, and transverse injection ahead of swept and unswept steps and strut bases. The results provide useful guidance for predicting self ignition in a variety of applications. The likely regions for self ignition in a combustor are given in order of merit.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TP-1457 , L-12678
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  • 9
    Publication Date: 2019-06-27
    Description: Determining electron concentration in flowing plasma in presence of accelerating and evaporating water droplets
    Keywords: PHYSICS, PLASMA
    Type: NASA-TN-D-6007 , L-6756
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  • 10
    Publication Date: 2019-07-13
    Description: The length of the entry blackout period during descent of the Viking Lander into the Mars atmosphere is predicted from calculated profiles of electron density in the shock layer over the aeroshell. Nonequilibrium chemistry plays a key role in the calculation, both in the inviscid flow and in the boundary layer. This is especially true in the boundary layer contaminated with ablation material, for which nonequilibrium chemistry predicts electron densities two decades lower than the same case calculated with equilibrium chemistry.
    Keywords: COMMUNICATIONS
    Type: AIAA PAPER 73-260 , Aerospace Sciences Meeting; Jan 10, 1973 - Jan 12, 1973; Washington, DC
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