Boundary layer over a rotating disk sector

Analysis is presented for the laminar incompressible boundary layer flow over a rotating plane sector of wide angle (but significantly less than a full circle). It is shown that the flow changes from the leading to the trailing edge from that characteristic of thin narrow blades to that characteristic of axisymmetric disks. Finally, a momentum-integral solution of the wake flow is presented in order to estimate the disturbance that the wake causes at the leading edge.