Research Article
Aerodynamic Optimization Design of a Supersonic Compressor Rotor with High Pressure Ratio
Figure 17
Mach number contours of 90% span at the near-stall point.
(a) 3D-opt rotor |
(b) Shroud+1 mm |
(c) Shroud+2 mm |
(d) Shroud+3 mm |
(e) Shroud+4 mm |