Analysis of Transonic Normal Shock-Boundary Layer Interaction and Comparisons with Experiment.

Recent progress in the development and application of an analytical theory for non-separating transonic interactions is described. The theory is an approximate multi-layered model leading to a mixed transonic rotational small disturbance flow boundary value problem solved by Fourier transformation methods. Among the results discussed are: (a) a parametric study of Reynolds number effects yielding universal incipient separation curves for weak normal shock interactions; (b) upstream influence and boundary layer thickening; (c) lateral pressure gradient effects and post-shock expansion regions; (d) detailed comparisons with pressure distribution data from both channel flow experiments and supercritical wing test data. (Author)