Abstract
A it experimental study of film cooling with subsonic gas injection into a ma instream witha Mach number of 2.90 is reported. Air, used us both the mainstream and secondary fluids, is injected normal to the surface of a flat plate through a short porous section into a two-dimensional turbulent boundary layer. The secondary fluid enters the boundary layer with a mass velocity which ranges from 0.0085 to 0.0223 of the free-stream value. The adiabatic wall temperatures are presented as the film-cooling effectiveness. The results of the present study, when the proper choice is made for the reference stale used to account for fluid property variations across the high-speed boundary layer, are in good agreement with previous investigations in incompressible flows.
| Original language | English (US) |
|---|---|
| Pages (from-to) | 584-588 |
| Number of pages | 5 |
| Journal | Journal of Manufacturing Science and Engineering, Transactions of the ASME |
| Volume | 90 |
| Issue number | 4 |
| DOIs | |
| State | Published - 1968 |