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

Figure 18

Surface pressure distribution on the blades during the forward flight at the mapped Chebyshev points varying from seven, nine, and eleven in total. Surface pressure distribution on the blades at the reconstructed at 11 mapped Chebyshev points.

(a) 7 Chebyshev points

(b) 9 Chebyshev points

(c) 11 Chebyshev points

(d) Reconstructed from the 11 points to eighteen