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Perturbations of the streaky structure at the initial stage of its breakdown


Perturbations of the streaky structure at the initial stage of its breakdown

The Movie show Matlab procesing of the experimental data obtained in a subsonic wind tunnel. The testing model is a wing with airfoil C-16, chord c = 707 mm, and sweep angle of 45°. The wing is placed horizontally in the facility test section. The oncoming-flow turbulence level is within 0.1%. The wall flow characteristics are determined through hot-wire measurements using single-wire and V-shaped probes, which are displaced in three directions by an automatic traversing system. At each measurement point, the recording of a signal of the hot-wire probe is synchronized with the generator of secondary oscillations.

Read more in Instability of a swept-wing boundary layer modulated by stationary flow perturbations.

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