Abstract
The Ohio State 6” × 22” Unsteady Transonic Wind Tunnel was used to study different methods of experimentally capturing the time-varying location of a shock wave on a NACA 0012 airfoil. The unsteady wind tunnel enables a freestream Mach number oscillation of 0.51 ± 0.1 for a Reynolds number range of 17 – 43 million per meter. Fast-response pressuresensitive paint (PSP) and particle image velocimetry (PIV) were evaluated for their ability to capture time-accurate location of the oscillating shock wave. Unsteady surface pressure and temperature measurements were made using a fast-response bi-luminophore pressuresensitive paint with a single-shot intensity-based technique. This method allows for high spatial resolution surface pressure and temperature maps. Phase-locked planar particle image velocimetry data were also acquired in this experiment, demonstrating an ability to resolve a moving shock. These advanced diagnostic tools enable detailed understanding of the impact of time-varying compressibility both on and off the airfoil surface. The information obtained with each of these techniques is compared in terms of spatial resolution and accuracy with data acquired via surface pressure taps. A NACA 0012 airfoil was tested at 9, 10 and 11 degrees angle of attack and at low reduced frequencies.
Published Version
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