Research Article
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°).
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