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drag of circular cylinder sections
*subcritical Reynolds number drag= Cd 1.2
*supercritical Reynolds number drag = Cd 0.40
The data is cited in Hoerner's book "AERODYNAMIC DRAG",and the actual research is from the German DVL,1934
*With a "optima" fairing (not shown),the drag is as low as:
^ Cd 0.35 subcritical
^ Cd 0.05 supercritical
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