SKIN-FRICTION MEASUREMENTS AND CALCULATIONS ON A LIFTING AIRFOIL

A new technique for measuring skin friction was employed to help docum ent the Bow on an airfoil at angles of attack from -0.5 to 11.5 deg. S urface pressures were also measured on both the wing and wind-tunnel w alls. The experiment was conducted at a freestream Mach number of 0.2 and Reynolds numbers of 0.6, 2, and 6 x 10(6). The objective of the st udy was to provide data and boundary condition information sufficient for the validation of numerical simulations. Such a simulation of the experiment was conducted using the INS2D Navier-Stokes code with the s hear-stress-transport turbulence model. The computations provide a goo d description of both laminar and turbulent shear levels, except for t urbulent Bow on the top surface of the wing at the higher angles of at tack.