The results of an experimental investigation of shock-induced stall and leading-edge stall on a 64A010 airfoil section are presented. Advanced nonintrusive techniques--laser velocimetry and holographic inteferometry--were used in characterizing the inviscld and viscous flow regions. The measurements include Mach contours of the inviscid flow regions, and mean velocity, flow direction, and Reynolds shear stress profiles in the separated regions. The experimental observations of this study are

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... evant to efforts to improve surfacepressure prediction methods for airfoils at or near stall. C CL ! L N P Rec Ruv u um u X Y Ol 6 0 p II p 7 Nomenclature = chord length of airfoil =skin friction coefficient, rw/½p_.u_ = lift coefficient, L / ½p_ u_ = local pressure coefficient, Co -p® ) / ½p® u_ = Gladestone-Dale constant = Prandtl's mixing length = optical path length = total number of velocity realizations --pressure = Reynolds number based upon airfoil chord length = uv correlation coefficient, u' v' / (u') (v') = velocity component in the streamwise direction = minimum velocity across wake = velocity component in the normal direction = coordinate in the streamwise direction = coordinate in the normal direction = angle of attack = viscous layer thickness = fringe shift in interferogram = flow angle, arctan 6/_ = laser wavelength = kinematic viscosity = Cole's wake parameter = fluid density = shear stress = weighting factor for velocity biasing Subscripts e = conditions at edge of viscous layer i =/th velocity realization s = surface w = conditions at the surface o, = freestream conditions Superscripts (') = fluctuating quantity ( --) = time-averaged quantity (') = rms value of quantity