Navier-Stokes calculations have been performed for a supercritical airfoil at a transonic design condition and at a subsonic condition. Wind-tunnel pressure-rail measurements were employed as boundary data in the calculations to account for wall-interference effects. A fine mesh was used so that most details of the flows were resolved, particular attention having been given to the trailing-edge region. Detailed comparisons are made with the experimental data. Good agreement was obtained on the airfoil except at the trailing edge where separation occurred. Flow details in the trailing-edge region are examined and differences are shown to be attributable to the turbulence model employed.
Comparison of supercritical airfoil flow calculations with wind-tunnel results
01.07.1983
Aufsatz (Konferenz)
Keine Angabe
Englisch
Comparison of supercritical airfoil flow calculations with wind tunnel results
Tema Archiv | 1985
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