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When the Mach number is slowly increased in straight and level flight the first shock waves will occur:
  • A
    On the upper wing, close to the leading edge.
  • B
    On the lower surface of the wing.
  • C
    On the upper wing, where it is thickest.
  • D
    Somewhere on the horizontal tail.
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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