airfoilprep.Airfoil.createDataGrid

Airfoil.createDataGrid()

interpolate airfoil data onto uniform alpha-Re grid.

Returns:

alpha : ndarray (deg)

a common set of angles of attack (union of all polars)

Re : ndarray

all Reynolds numbers defined in the polars

cl : ndarray

lift coefficient 2-D array with shape (alpha.size, Re.size) cl[i, j] is the lift coefficient at alpha[i] and Re[j]

cd : ndarray

drag coefficient 2-D array with shape (alpha.size, Re.size) cd[i, j] is the drag coefficient at alpha[i] and Re[j]