[aerohead]

Thanks freebeard!
From the fuselage chart it looks like the 60% truncation will cause a 28+% drag increase,so we'd be looking at Cd 0.284 with that tail chop.
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As to the nose truncation with leading edge radii,according to Hucho,that minimum would get you your flow attachment,and further rounding would net zero additional drag reduction.
************* The caveat is with 'crosswinds'. In a yawed flow condition (which is the statistical norm for N.America) the full,bulbous nose would have a distinct drag advantage.(think Oscar Mayer Weinermobile)