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Assume a transition Reynolds number of 500,000. For this case, calculate the percentage of drag that is due to :flow separation (form drag).

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In reality, the boundary layer on the airfoil discussed in Prob. 5.37 is neither fully laminar nor fully turbulent. The boundary layer starts out as laminar, and then transitions to turbulent at some point downstream of the leading edge (see the discussion in Sec. 4.19.) Assume that the critical Reynolds number for transition is 650,000. […]

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