Abstract
A compressor cascade was tested in a low speed two-dimensional cascade wind tunnel. The measurements of flow field on blade surface were made at the cascade inlet and exit. Boundary layer development was analyzed under different inlet flow conditions. The pressure gradient on blade surface and their effects on transition from laminar flow to turbulent flow was studied numerically at different inlet Mach numbers and incidences. By means of the experimental data, the viscous boundary layer transition on blade surface was studied in detail. It is very helpful for better understanding of the complex boundary layer transition mechanics.
| Original language | English |
|---|---|
| Pages (from-to) | 64-68 |
| Number of pages | 5 |
| Journal | Tuijin Jishu/Journal of Propulsion Technology |
| Volume | 20 |
| Issue number | 3 |
| State | Published - Mar 1999 |