MEASUREMENTS ON A DIVERGENT TRAILING EDGE AIRFOIL

摘要

A subsonic airfoil model was designed to represent flow in the vicinity of the trailing edge of a supercritical divergent trailing edge airfoil for commercial aircraft in transonic cruise. Results, calculated with a combination of an interactive boundary-layer and invicid Euler method and from a transonic Reynolds Averaged Navier-Stokes solution procedure, were combined to configure a model with flow downstream of the trailing edge which is similar to that downstream of blunt trailing edges in transonic flight. A combination of flow visualization and measured distributions of surface pressure are presented, first, to verify the two-dimensional structure of the mean flow over the center section of the model, and second, to characterize the flow structure. Specific attention is given to flow structure of the recirculation region immediately behind the blunt base, with the focus of predicting flow in this region. Comparisons between calculated and measured surface pressures are in good agreement except for details on the blunt base of the model, and the implications of this for future measurements of turbulence quantities is described.