Total Pressure in Laval Nozzle
Hi, I am working over a convergent - divergent supersonic nozzle. The fluid is combustion / exhaust gases.
The contour of total pressure at throat region shows an increased value, which is greater than the value of total pressure at inlet. The total pressure then decreases in the divergent portion.
I need to ask whether it is possible that total pressure of a flow increases more than its initial value, at any point during the flow. The flow is viscid, 2D. Decrease in total pressure is understandable, because of friction / viscous losses, but I have been unable to understand an increase in total pressure. Please advise!
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