Transonic Static Aeroelastic Numerical Analysis of Flexible Complex Configuration Wing

Figure 8

Effects of static aeroelasticity on wing surface pressure. (a) Rigid wing (α = −4°). (b) Flexible wing (α = −4°). (c) Rigid wing (α = 0°). (d) Flexible wing (α = 0°). (e) Rigid wing (α = 4°). (f) Flexible wing (α = 4°).

(a)

(b)

(c)

(d)

(e)

(f)