Abstract
Nomenclature CD = drag coefficient CL = lift coefficient Cf = zero angle-of-attack lift curve slope Cm° = moment coefficient calculated about airfoil quarter-chord Cp — pressure coefficient C3,C] = terms used in Barnwell's boundary-layer thickness equation q = local boundary-layer edge velocity RN = Reynolds number s = airfoil arc length Ue = transformed boundary-layer edge velocity k^sep = value of Ue at separation point SP = separation parameter X = Cartesian chordwise coordinate -^sep = value of X at the separation point a = angle of attack of airfoil with respect to the freestream <5 = boundary-layer thickness <5sep = boundary-layer thickness at separation point 6 = local momentum thickness
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