Quote:
Originally Posted by sendler
There is some contradictory information between some of these charts. How is the round shape shown as the same cd as the airfoil at .09. You have posted other charts with the cd of a round rod much higher.
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These coefficients are in aeronautical terms,more like K-values based upon wetted area.The absolute numbers aren't really as important as their relation to one another.
The 2.5:1 streamline body of revolution produces a frontal area-based coefficient of drag of Cd 0.04.