Abstract
At transonic speeds, shock waves appear in flowfields about aircraft wings, in turbomachinery blade passages, and in air-breathing-engine inlets and diffusers. The interactions of these shock waves with turbulent boundary layers on the solid surfaces results in complex flow phenomena. In this paper, we study the shock/boundary interaction flows by numerically solving the mass-averaged compressible thin-layer Navier-Stokes equations in conjunction with a zero-equation Baldwin-Lomax and a two-equation turbulence model.
| Original language | English |
|---|---|
| Pages (from-to) | 485 |
| Number of pages | 1 |
| Journal | Developments in Mechanics |
| Volume | 13 |
| State | Published - 1985 |