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 ).
42.
In the above equations, \ mathbf u is the flow velocity vector, \ omega is the vorticity, v is the specific volume, p _ 0 is the stagnation pressure, T is temperature, s is specific entropy, h is specific enthalpy, \ mathbf { g } is specific body force, and n is the direction normal to the streamlines.
43.
:: : : Total pressure exists everywhere, and stagnation pressure only exists at stagnation points, but total pressure and stagnation pressure are equal ( except in the vicinity of shock waves . ) Seeing total pressure and stagnation pressure are equal, many authors who write about incompressible flows, and low speed flows, don't complicate things by talking about total pressure.
44.
:: : : Total pressure exists everywhere, and stagnation pressure only exists at stagnation points, but total pressure and stagnation pressure are equal ( except in the vicinity of shock waves . ) Seeing total pressure and stagnation pressure are equal, many authors who write about incompressible flows, and low speed flows, don't complicate things by talking about total pressure.
45.
:: : : Total pressure exists everywhere, and stagnation pressure only exists at stagnation points, but total pressure and stagnation pressure are equal ( except in the vicinity of shock waves . ) Seeing total pressure and stagnation pressure are equal, many authors who write about incompressible flows, and low speed flows, don't complicate things by talking about total pressure.
46.
A de Laval nozzle will only choke at the throat if the pressure and mass flow through the nozzle is sufficient to reach sonic speeds, otherwise no supersonic flow is achieved, and it will act as a Venturi tube; this requires the entry pressure to the nozzle to be significantly above ambient at all times ( equivalently, the stagnation pressure of the jet must be above ambient ).
47.
:If you simply the problem a bit, ignoring compressibility ( reasonable at these windspeeds ) and sofftis ( which I have no idea what they are ) it boils down to stagnation pressure, which is \ frac { 1 } { 2 } \ rho V ^ 2, where \ rho is the air density and V is the wind speed ( in metric units, please ! ).
48.
The Bernoulli equation applicable to incompressible flow shows that the stagnation pressure is equal to the dynamic pressure plus static pressure . " Total pressure " is also equal to dynamic pressure plus static pressure so, in incompressible flows, stagnation pressure is equal to total pressure . ( In compressible flows, stagnation pressure is also equal to total pressure providing the fluid entering the stagnation point is brought to rest isentropically .)
49.
The Bernoulli equation applicable to incompressible flow shows that the stagnation pressure is equal to the dynamic pressure plus static pressure . " Total pressure " is also equal to dynamic pressure plus static pressure so, in incompressible flows, stagnation pressure is equal to total pressure . ( In compressible flows, stagnation pressure is also equal to total pressure providing the fluid entering the stagnation point is brought to rest isentropically .)
50.
The Bernoulli equation applicable to incompressible flow shows that the stagnation pressure is equal to the dynamic pressure plus static pressure . " Total pressure " is also equal to dynamic pressure plus static pressure so, in incompressible flows, stagnation pressure is equal to total pressure . ( In compressible flows, stagnation pressure is also equal to total pressure providing the fluid entering the stagnation point is brought to rest isentropically .)
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