CFD calculations of the flow over an airfoil give an average drag coefficient of 0.0848 on a baseline mesh and 0.0872 on a mesh that has a uniformly 50% denser grid in all directions. Assuming the numerical method is uniformly third-order accurate, estimate the correct value of the drag coefficient to four decimal places of accuracy (+-0.0001)

ANS: 0.0882

Hint: Taylor series representation of finite difference methods and combine two Taylor series at different resolutions to solve this type of problem.

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