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What is Aircraft Drag Polar Analysis E374 & SD6060 about?

This document contains the results of aerodynamic calculations for two airfoils, E374 and SD6060-104-88, across a range of angles of attack. For each airfoil, lift coefficient, drag coefficient, pressure drag coefficient, and other values are reported at incremental angles of attack from 0 to 20 degrees. The calculations were performed using XFLR5 software at a Reynolds number of 150,000 and Mach number of 0.

Author

cjbdl

Language

EN