Propagation of Shock on NREL Phase VI Wind Turbine Airfoil under Compressible Flow

Figure 7

(a) Pressure contour at mach 0.11 and 𝛼=0^∘, (b) pressure contour at mach 0.8 and 𝛼=0^∘, and (c) static pressure distribution of S809 airfoil at 𝛼=0^∘.

(a)

(b)

(c)