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For a symmetrical airfoil drag coefficient at zero lift is 0.05 and induced drag coefficient is 0.0025. Find the total drag coefficient.

For a symmetrical airfoil drag coefficient at zero lift is 0.05 and induced drag coefficient is 0.0025. Find the total drag coefficient. Correct Answer 0.0525

Total drag coefficient = drag coefficient at zero lift + induced drag coefficient = 0.05+0.0025 = 0.0525.

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