Turbulence Amplification with Incidence at the Leading Edge of a Compressor Cascade

Abstract

Detailed measurements, with a two-component laser-Doppler velocimeter and a thermal anemometer were made near the suction surface leading edge of controlled-diffusion airfoils in cascade. The Reynolds number was near 700,000, Mach number equal to 0.25, and freestream turbulence was at 1.5% ahead of the cascade.

Keywords

• Compressors
• Boundary layers
• Separation bubbles
• Laser-Doppler velocimetry.