2 edition of Temperature distributions of a cesium-seeded hydrogen-oxygen supersonic free jet found in the catalog.
Temperature distributions of a cesium-seeded hydrogen-oxygen supersonic free jet
by National Aeronautics and Space Administration, Scientific and Technical Information Office, for sale by the National Technical Information Service in Washington, Springfield, Va
Written in English
|Statement||Shih-Ying Wang and J. Marlin Smith.|
|Series||NASA technical paper ; 1162, NASA technical paper -- 1162.|
|Contributions||Smith, J Marlin., United States. National Aeronautics and Space Administration. Scientific and Technical Information Office.|
|The Physical Object|
|Pagination||21 p. :|
|Number of Pages||21|
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Get this from a library. Temperature distributions of a cesium-seeded hydrogen-oxygen supersonic free jet. [Shih-ying Wang; J Marlin Smith; United States. National Aeronautics and Space Administration.
Scientific and Technical Information Office.]. Radial distributions of temperature were determined spectroscopically in a cesium- seeded, hydrogen-oxygen plasma jet. The plasma was generated at combustion cham- ber pressures ranging from 0.
5 to 2. 0 megapascals and for various seed ratios (1 to. Temperature distributions of a cesium-seeded hydrogen-oxygen supersonic free jet: Authors: Wang, S. Y coefficients for conditions of local thermodynamic equilibrium using particle densities generated by a two-dimensional free jet computer program.
Temperature results show the inherent effects of compression and expansion pressure waves. Temperature distributions of a cesium-seeded hydrogen-oxygen supersonic free jet.
By J. Smith and S. Wang. Abstract. The hydrogen-oxygen plasma was generated at combustion chamber pressures ranging from to megapascals and for various seed ratios (1 to 10 percent). The plasma was observed as the atmospheric exhaust from a Mach 2 Author: J.
Smith and S. Wang. Temperature distributions of a cesium-seeded hydrogen-oxygen supersonic free jet / By Shih-ying.
Wang, joint author. Marlin Smith and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office. Abstract. Issued Feb. Includes bibliographical of access: Internet.
Temperature measurements were performed in a shock-tunnel-generated free jet of hydrogen/oxygen reaction products diluted in argon with a nonsimultaneous, two-excitation-line planar laser-induced.
shock free flows up to low supersonic speeds and low heat transfer rate (Wilcox, ). When a cold supersonic jet (K) enters into a hot atmosphere of around K, it results in high heat transfer from the hot environment to the jet due to large temperature difference. Wilcox () recommended to use 𝑃 = for free shear flow and highCited by: 2.
Shock-wave interactions at impingement of impulsive supersonic jet upon an obstacle. Numerical investigation of induction-zone development in hydrogen-oxygen mixtures. Temperature distribution in free-piston compressors. The focus of this study is to design a combustion system able to sustain hypersonic flight at Mach 8.
A Dual-Mode Free-Jet combustion chamber design, first tested in by NASA, is being adapted to run on hydrogen fuel instead of ethylene while addressing the excessive thermal heat load. This study is part of the FAME (Flight at Mach Eight) project, with the primary objective to Author: Maxim Cooper, Ashish Alex Sam, Apostolos Pesyridis.
The process involved in chemical energy release by combustion in a supersonic, constant pressure, hydrogen-air laminar mixing layer was studied computationally, with. A series of firing tests of the hydrogen-fueled detonation ramjet model is performed in the pulsed wind tunnel at the approach air stream Mach number ofthe stagnation temperature of K, and the observation time of 50 ms in the range of the overall air-to-hydrogen ER Cited by: 7.
An axial flow gas turbine stage develops MW at a mass flow rate of kg/s. At the stage entry the stagnation pressure and temperature are kPa and °C, respectively. The static pressure at exit from the nozzle is kPa and the corresponding absolute flow direction is 72° to the axial direction.
64 Combustion Fundamentals Chap. 2 The large quantity of nitrogen diluent substantially reduces the mole fractions of the combustion products from the values they would have in its absence.
Example Combustion ofOctane in Air Detennine the stoichiometric fuel/air mass ratio and product gas composition for combus tion ofoctane (CSH1S) in air.
Fei Deng, Ning Liu, Xiang-yan Zhang and Liu-yi Zhang Numerical analysis of hydrogen-oxygen combustion in Combustion Light Gas gun with detailed kinetic mechanisms, ().Cited by: The results of investigation of the plume structure in the case of diffusion combustion of hydrogen in a cocurrent supersonic high-enthalpy off-design air jet are presented.
Based on the registration of radiation within the wavelength range of – nm across and along the flame, a three-dimensional tomographic reconstruction of the plume was obtained, Cited by: 6. Supersonic Combustion in Air-Breathing Propulsion Systems for Hypersonic Flight (TDLAS) (Liu et al.
) to measure spatiotemporal distributions of temperature and water vapor concentration in the burnt gases at the combustor exit. As of the date of publication of this article, however, the data acquired during the flight test are of Cited by: They USE shock waves for chemical kinetics studies, for materials studies, and smashing kidney stones; they STUDY the phenomena associated with flows involving shock waves, such as supersonic flow, explosions, detonations, volcanic eruptions, and, in this symposium, even such with-it topics as impact of Shoemaker-Levy on Jupiter and blast waves.
Temperature and composition of a plasma obtained by seeding a cyanogen-oxygen flame with cesium (NASA technical note) [Hord, Richard A] on *FREE* shipping on qualifying offers. Temperature and composition of a plasma obtained by seeding a cyanogen-oxygen flame with cesium (NASA technical note)Author: Richard A Hord.
Ultraviolet photoelectron spectroscopy (UPS) and electron spectroscopy by deexcitation of metastable noble gas atoms (MDS) were used to follow the continuous oxidation of Cs films.
While UPS has a finite information depth, MDS probes only the properties of the outermost atomic layer. Small doses of O 2 cause the formation of a ‘‘monolayer’’ of Cs 1 1 O 3 in which the O 2 Cited by: ESTIMATES OF OPTIMAL OPERATING CONDITIONS FOR HYDROGEN-OXYGEN CESIUM-SEEDED MAGNETOHYDRODYNAMIC POWER GENERATOR J.
Marlin Smith and Lester D. Nichols Lewis Reseurch Center Cleuelund, Ohio 35 NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON, D.
American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA The problem of continuous spin detonation in a supersonic flow in a flow-type annular combustor is considered in a two-dimensional unsteady formulation.
The dynamics of the detonation wave in a hydrogen-oxygen mixture with isentropic and shock-wave compression of the flow in the input diffuser is studied.
It is shown that the mass flow rate of the mixture Cited by: 7.Expanding supersonic plasma jet generated in dc water-stabilized arcs Co-investigator Provider: Temperature Distribution of Asymmetrically Current Carrying Thermal Plasma Jet.
Proceedings of 17th Symposium on Plasma Physics and Technology. Study of non-equilibrium effects in hydrogen-oxygen thermal plasma JET. International Symposium on.