Two-Pulse STB investigation of shock wave boundary layer interaction flow over fluttering OAT15A wing

Kurzfassung

A two-pulse two-cameras particle tracking investigation of the transonic flow over an OAT15A fluttering wing model has been carried out in the framework of HOMER work package 5 (WP5, Task 5.2). The objective of the investigation is to gain insight in the fluid dynamic of the shock wave boundary layer interaction and to generate an experimental database suitable for the validation of fluid-structure interaction (FSI) codes. The measurement is carried out in the Trisonic Wind Tunnel Munich (TWM); a 2D rigid wing model (150 mm chordwise, 298 mm spanwise) is mounted on a spring to allow one torsional degree of freedom (Fig 1-top-left). The Mach number of the incoming flow is 0.74 and the angle of attack in wind-off condition 7.2°.