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Just above the critical Mach number the first evidence of a shock wave will appear at the:
  • A
    leading edge of the wing.
  • B
    upper side of the wing.
  • C
    lower side of the wing.
  • D
    trailing edge of the wing.
At Critical Mach number (MCRIT), somewhere on the profile, local sonic speed is reached. This is the point corresponding to maximum thickness at the upper side of the wing, as the flow is the fastest there. So the flow velocity reaches and slightly exceeds sonic speed, thus behind this point a normal shock wave occurs.

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