Abstract
The pressure distribution for circular-arc airfoil calculated with inviscid theory is generally in good agreement with the experiments over the surface of the airfoil except for the vicinity of the surface shock wave. The said discrepancy in the surface pressure distribution near the shock wave can be considered by the interaction of shock wave with boundary layer. As there is a strong coupling between the inner boundary layer and the outer inviscid flow, the solution must be developed simultaneously in both regions. In the present transonic investigation, a boundarylayer integral approach is combined with a finitedifference relaxation method to calculate the viscous interactions. The pressure distribution is obtained for the attached turbulent flow on circular-arc airfoil at zero angle of attack, and the results remarkably agrees with the experiment of KNECHTEL.
