Transition Effect on the Flow Dynamics in a Compressor Blade Passage

Table 4

RMS of average shock oscillations and shock amplitude for flow cases with roughness.

Flow case	A (mm)	RMS (mm)
Ref-laminar	4.37	1.21
X/C = 0.11, Ra = 8	4.84	1.33
X/C = 0.11, Ra = 10	3.96	1.04
X/C = 0.11, Ra = 12	4.84	1.07
X/C = 0.16, Ra = 12	4.71	1.54
X/C = 0.16, Ra = 16	5.04	1.52
X/C = 0.16, Ra = 20	4.45	1.20
X/C = 0.21, Ra = 12	5.48	1.57
X/C = 0.21, Ra = 16	6.28	1.85
X/C = 0.21, Ra = 20	4.63	1.24