Comparison of Boundary Layer Calculation for a Wing: The May 1978 Stocholm Workshop Test Case

摘要

Eight calculation methods for determining three-dimensional turbulent boundary layers were compared. All methods were applied to the same test case which was designed to simulate flow over a wind tunnel model wing. Geometry and free stream conditions were chosen to be representative, yet to yield a relatively simple compressible (subsonic) boundary layer with only moderate three-dimensionality and spanwise variation. Wing root, tip, and leading edge regions were excluded. Two wing incidences were considered. The main comparison of the calculation methods involved comparing four parameters appearing in the integral equations of motion in streamline coordinates. Despite the simplicity of the test case, disproportionately large differences were evident among the outputs of the eight programs (as much as 10 percent or 20 percent typically). Possible explanations for these discrepencies are suggested.