Results 311 to 320 of about 95,741 (349)

Electron temperature measurements along a stagnation point streamline

The Physics of Fluids, 1973
Experimental observations of the electron temperature profile along a stagnation point streamline have been found to be in good agreement with the theory developed for the case where the interaction between an electron thermal layer and a viscous shock layer was considered.
Michio Nishida, Shuji Sugimoto
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Solar Collector Durability Evaluation by Stagnation Temperature Measurements

Journal of Solar Energy Engineering, 1983
An analytical and experimental investigation was undertaken to evaluate an alternative method for measuring the thermal degradation of materials used in flat-plate collectors. This test method is based on measuring the temperature of the absorber under a no-flow condition before and after prolonged exposure.
A. G. Dawson, W. C. Thomas, D. Waksman
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Development of a stagnation temperature probe for supersonic combustion flows

High Temperatures-High Pressures, 1995
As part of the French hypersonic programme (PREPHA), a probe has been developed to measure the stagnation temperature in an air/hydrogen supersonic combustion ramjet engine (SCRAMJET)
Olivier Pin, Jean-Marie Badie, Gabriel Olalde, Michel Clément   +3 more
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Stagnation-Point Heat Transfer in a High-Temperature Inert Gas

The Physics of Fluids, 1962
Stagnation-point similarity solutions of the laminar boundary-layer equations are calculated for a thermally and calorically perfect gas with Prandtl number ⅔ and viscosity proportional to a power of the absolute temperature (μ ∝ T1−α). The parameter α is varied from 0 to 0.5, and the enthalpy ratio across the boundary layer from 0.01 to 0.80.
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An experimental investigation of hypersonic stagnation temperature probes

1959
NOTE: Text or symbols not renderable in plain ASCII are indicated by [...]. Abstract is included in .pdf document. An experimental investigation of single-shielded hypersonic stagnation temperature probes was conducted in the GALCIT Leg No.1 hypersonic wind tunnel and in the Jet Propulsion Laboratory 12-inch supersonic wind tunnel.
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Stagnation temperature and molecular weight effects in jet interaction

AIAA Journal, 1969
The purpose of this study was to investigate the effect of injectant stagnation temperature and molecular weight variation on the flowfield generated from secondary injection of a gas normal to a supersonic stream. Experiments were conducted at a primary stream Mach number of 2.80 in the Naval Postgraduate School supersonic wind tunnel.
L. CHRANS, D. COLLINS
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Laminar Stagnation-Point Heat Transfer for a Two-Temperature Argon Plasma

AIAA Journal, 1984
A theory for the heat transfer to the stagnation-point boundary layer of an axisymmetric blunt body in a subsonic two-temperature argon plasma flow was developed. Two-temperature transport properties were calculated from the rigorous kinetic theory and are employed in solving the multifluid problem formulated with a wall sheath boundary condition.
Bose, T. K., Seeniraj, R. V.
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Total radiation measurements at the stagnation point of blunt bodiesat stagnation temperatures to 15,000 deg K

3rd Aerodynamics Testing Conference, 1968
Blunt bodies stagnation point radiation intensity measurements in supersonic flow at very high stagnation temperatures generated by constricted arc ...
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Measurements of Stagnation-Point Temperature with High-g Telemetry

IEEE Transactions on Aerospace and Electronic Systems, 1968
Measurement of phenomena associated with free-flight models in ballistic ranges has been made possible with the development of a stable on-board miniaturized telemetry system that will withstand large gun-launch accelerations. The results of body temperature measurements behind the stagnation point with thin-film temperature gauges are presented and ...
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Temperature-dependent heat sources or sinks in a stagnation point flow

Applied Scientific Research, 1961
An analytical study has been made to determine the heat transfer characteristics of a stagnation point flow in which there are temperature-dependent heat sources or sinks. Results have been obtained for both strong and weak sources or sinks for a Prandtl number of 0.7.
Sparrow, E. M., Cess, R. D.
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