Numerical solutions to turbomachinery flows have increased in both complexity and accuracy. Conventional measurement techniques cannot always adequately test the detailed solutions available. Holographic interferometry can provide such data and is of particular value in the mainstream region of a two-dimensional flow. The transonic flow around a wedge profile has been used to produce examples of several features of current interest. On the wedge surface a strong leading edge shock is seen followed by a Prandtl-Meyer expansion. On the tunnel sidewall the flow first experiences an expansion and then a boundary layer separation. The flow around the wedge has been calculated using an inviscid time marching program. It is shown that by making simple changes to the geometric data used by the program a good agreement can be obtained despite the presence of a separated flow region.

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