Letter to Hsue Shen Tsien On Air Foil of Minimum Drag in Supersonic Flow
Letter to Hsue Shen Tsien On Air Foil of Minimum Drag in Supersonic Flow
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I do not see, however, how this should operate in detail. For subsonic flow one could say that the stagnation pressure, which is essentially assumed at the back of the body, is lower than that in front due to the action of viscosity. I do not notice, however, how such an argument could be applied, to supersonic flow to explain the occurrence of a sub-atmospheric pressure at the back.
There is another reason why the flow pattern assumed in con- dition III might not be correct under certain circu...mstances. The pressure p. Behind the trailing shock must eventually adjust itself to the value p* at infinity. This, I imagine can be done by the faint waves that result from reflection at the leading shock front and crossing the trailing shock front. If the terminal pressure P t is rather low, I feel that adjustment to p, takes place in a difference manner, viz. By detachment of the flow (combined with a shock) before the rear tip is reached. This would then correspond to the situation in nozzle flow where detachment takes place inside the nozzle when the shockless flow would have too low a pressure at the exit.
What to read after Letter to Hsue Shen Tsien On Air Foil of Minimum Drag in Supersonic Flow?
You can find similar books in the "Read Also" column, or choose other free books by Kurt Otto Friedrichs to read onlineMoreLess
To quickly assess the difficulty of the text, read a short excerpt:
I do not see, however, how this should operate in detail. For subsonic flow one could say that the stagnation pressure, which is essentially assumed at the back of the body, is lower than that in front due to the action of viscosity. I do not notice, however, how such an argument could be applied, to supersonic flow to explain the occurrence of a sub-atmospheric pressure at the back.
There is another reason why the flow pattern assumed in con- dition III might not be correct under certain circu...mstances. The pressure p. Behind the trailing shock must eventually adjust itself to the value p* at infinity. This, I imagine can be done by the faint waves that result from reflection at the leading shock front and crossing the trailing shock front. If the terminal pressure P t is rather low, I feel that adjustment to p, takes place in a difference manner, viz. By detachment of the flow (combined with a shock) before the rear tip is reached. This would then correspond to the situation in nozzle flow where detachment takes place inside the nozzle when the shockless flow would have too low a pressure at the exit.
What to read after Letter to Hsue Shen Tsien On Air Foil of Minimum Drag in Supersonic Flow?
You can find similar books in the "Read Also" column, or choose other free books by Kurt Otto Friedrichs to read onlineMoreLess
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