Question: for a 6 4 2 - 2 1 5 airfoil ( see naca tr - 8 2 4 ) determine the following being as accurate

for a 642-215 airfoil (see naca tr-824) determine the following being as accurate as possible: a) lift coefficient at 0 and 8 degrees, b) moment coefficient at 0 and 8 degrees, c) to calculate lift curve slope, center of pressure location

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