Cascade performance of a double arc compressor blade at low Reynolds number
A description of a recently-developed cascade test section as well as an outline of a computer program using the simultaneous solution technique to solve the freestream and boundary layer for a quasi three-dimensional flow through a blade passage is presented. Experimental results for the velocity distributions along the blade surface, the flow deflection, and the profile loss are compared to the data obtained from the computer program for different angles of incidence.
The comparison of experimental and theoretical results is in general agreement except for the losses and deflection angles at large positive and negative incidence angles. However, the experimental equipment as well as the computer program need to be improved, since some end-wall boundary layer effects are apparent.