Abstract
A shock tube with a rectangular test section is utilized to study the transonic flow about an airfoil model of a constant chord length. Upstream moving pressure waves are observed in experiment as well as in numerical simulation of a supercritical airfoil flow for different flow regimes. Both experimental and numerical results show that the observed waves are coupled with vortex generation in the boundary layer as well as wake fluctuations. The measured wave frequencies are in the order of 1-2 kHz. Using statistical means the wave speeds and wave propagation direction could be determined.
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