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Aerospace Stagnation pressure for attached shock

  1. Apr 7, 2009 #1
    Hi, does anyone know the definition of "stagnation pressure" at the tip of a slender body
    with attached oblique shockwave?

    Since the shockwave is completely "attached" to the pointing tip, I think that there is
    no flow "behind" the shock at the tip.
    So I proceed to think that the stagnation pressure at the tip should be stagnation pressure
    of the freestream flow without any pressure loss from the shock.

    I have been looking for the answer for days but surprisingly there is not a single source
    that answers my question.

    I appreciate any help.
     
  2. jcsd
  3. Apr 29, 2009 #2
    I think that is a pretty good estimate. although, sometimes when you zoom in on the tip you still see a small "bow" wave in front of the tip. From a distance the shock wave seems attached.
     
  4. May 1, 2009 #3
    I too think that you are right. the stagnation pressure of freestream will be same as that of the stagnation pressure at the tip
     
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