Abstract
An experimental study has been conducted to examine the control effectiveness of dimples on the glancing shock wave turbulent boundary layer interaction produced by a series of hemi-cylindrically blunted fins at Mach numbers 0.8 and 1.4, and at angles of sweep 0°, 15°, 30° and 45°. Schlieren photography, oil flow, pressure sensitive paints, and pressure tappings were employed to examine the characteristics of the induced flow field. The passive control technique used a series of 2 mm diameter, 1 mm deep indents drilled across the hemi-cylindrical leading edge at angles 0°, 45°and 90°. The effects of dimples were highly dependent on their orientation relative to the leading edge apex, and the local boundary layer properties. © 2007 Springer-Verlag.
| Original language | English |
|---|---|
| Pages (from-to) | 323-335 |
| Number of pages | 12 |
| Journal | Shock Waves |
| Volume | 17 |
| Issue number | 5 |
| DOIs | |
| Publication status | Published - Feb 2008 |
Keywords
- Dimples
- Passive flow control
- Pressure sensitive paint
- Transonic and supersonic flows