Helicopter Rotor Flow Analysis Using Mapped Chebyshev Pseudospectral Method and Overset Mesh Topology

Figure 17

Pressure coefficients at the 0.89 radial location during the forward flight with an azimuth angle varying from 30 deg to 180 deg by 30 deg.

(a) = 30 deg

(b) = 60 deg

(c) = 90 deg

(d) = 120 deg

(e) = 150 deg

(f) = 180 deg