Pressure distribution and schlieren for various locations of transonic compressor profiles

One of the primary objectives of the EU TFAST and TEAMAero projects is to study the shock wave and boundary layer interaction on the suction side of the transonic compressor blade. In this context, the test section is designed and assembled at the IMP PAN laboratory to replicate the flow structure in a transonic compressor cascade.

The system's sensitivity to variable parameters in the test section is crucial for achieving the design conditions and ensuring that the flow is influenced solely by the target parameter under study.

The provided data pertains to a study on the system's sensitivity to small changes in the position of the profiles relative to the nozzle (~±2% x/c). The results indicated that the profile position does not significantly alter the overall flow structure or the inflow Mach number. However, it affects the Mach number distribution over the lower profile, particularly upstream of the passage shock within the range of 0.3-0.4x/c.

Data can be used for CFD validation and sensitivity study. The pressure files and schlieren images are grouped by date.