Study of Sweep and Induced Dihedral Effects in Subsonic Axial Flow Compressor Passages—Part II: Detailed Study of the Effects on Tip Leakage Phenomena

Figure 5

Axial velocity coefficient contours on blade-to-blade planes 1.5 mm from the rotor tip at 𝜙 = 0.50.

(a)

(b)

(c)

(d)

(e)

(f)

(g)

(h)

(i)