Transonic Static Aeroelastic Numerical Analysis of Flexible Complex Configuration Wing

Figure 6

Comparison between numerical computation and wind tunnel test. (a) C_L∼α. (b) C_m∼α. (c) Δ (z)∼α (front wing). (d) Δ (z)∼α (rear wing).

(a)

(b)

(c)

(d)