Results 301 to 310 of about 93,173 (332)

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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A General Expression for the Isentropic Stagnation Temperature of a Fluid

Nature, 1964
THE stagnation temperature of a fluid is commonly represented by the expression: where T, U and cp denote the temperature, velocity and specific heat at constant pressure, and the subscripts 0 and ∞ refer to the stagnation point and free stream, respectively.
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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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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.
openaire   +2 more sources

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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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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Simultaneous Measurements of Temperature and CO Concentration in Stagnation Stabilized Flames

Flow, Turbulence and Combustion, 2012
An impinging jet burner was developed to investigate flame-wall interactions (FWI) using laser based diagnostics. CO concentrations were measured with two-photon laser-induced fluorescence (LIF) in combination with coherent anti-Stokes Raman spectroscopy (CARS) gas phase temperature measurements. Besides being the principal factor in chemical kinetics,
Avinash Singh, Markus Mann, Thilo Kissel, Jan Brübach, Andreas Dreizler   +4 more
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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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Fuel Stagnation Temperature Effects on Mixing with Supersonic Combustion Flows

Journal of Propulsion and Power, 1997
An experimental study of the effect of fuel stagnation temperature on mixing in a supersonic hydrogen-air flame is described, The combustor consisted of a constant-area rectangular duct with a centrally located fuel-injection strut that spanned the width. A high-enthalpy stream of air was supplied by a free-piston shock tunnel, and heated hydrogen fuel,
Wendt, MN, Stalker, RJ, Jacobs, PA
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