For many purposes in compressible flow, the stagnation enthalpy or stagnation temperature plays a role similar to the stagnation pressure in incompressible flow.
12.
With all solar thermal collector systems there is a potential risk that the solar collector may reach an equilibrium or stagnation temperature higher than the maximum safe operating temperature.
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Solving the differential equation leads to the relation shown below, where T 0 * is the stagnation temperature at the throat location of the duct which is required for thermally choking the flow.
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:Assuming a uniform stagnation temperature distribution, do a path integral around the Earth ( making sure to take compressibility into account ), then hop twice on your left leg while making clucking noises.
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Since the flow is isentropic, the stagnation properties like stagnation pressure ( p _ 0 ), stagnation temperature ( T _ 0 ) and stagnation density ( \ rho _ 0 ) remain constant.
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Stagnation temperatures are encountered under conditions of high radiation while no heat transfer fluid is flowing through the collector, for example during power failures, component failures, servicing, energy storage capacity limitations, or periods when little hot water is extracted from the system.
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Hypersonic flows are typically categorized by their total energy, expressed as total enthalpy ( MJ / kg ), total pressure ( kPa-MPa ), stagnation pressure ( kPa-MPa ), stagnation temperature ( K ), or flow velocity ( km / s ).
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In addition to the increase in afterburner exit stagnation temperature, there is also an increase in nozzle mass flow ( i . e . afterburner entry mass flow plus the effective afterburner fuel flow ), but a decrease in afterburner exit stagnation pressure ( owing to a fundamental loss due to heating plus friction and turbulence losses ).
19.
Where T is the total, or stagnation temperature of the rotating gas at radial position \ vec r, the absolute gas velocity as observed from the stationary frame of reference is denoted with \ vec v; the angular velocity of the system is \ vec \ omega and c _ p is the isobaric heat capacity of the gas.
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In aviation, stagnation temperature is known as "'total air temperature "'and is measured by a temperature probe mounted on the surface of the aircraft . The probe is designed to bring the air to rest relative to the aircraft . As the air is brought to rest, kinetic energy is converted to internal energy.
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