Aerodynamic Optimization Design of a Supersonic Compressor Rotor with High Pressure Ratio

Figure 27

Mach number contours for 90% span at the design point.

(a) Tip-forward +0.30

(b) Lengthen+0.05

(c) Lengthen+0.10

(d) Lengthen+0.15

(e) Lengthen+0.20