Wind Tunnel Testing on Start/Unstart Characteristics of Finite Supersonic Biplane Wing

Figure 8

Schlieren images of flow field around model A (AR = 0.75, 𝛼=0^∘, 𝛽=0^∘, and 𝜙=0^∘). The images for 0.3≤𝑀_∞≤0.8 were obtained from case  1, and those for 1.0≤𝑀_∞≤1.3 were obtained from case  2. Arrows in (d) and (e) indicate reflected waves on the inner window.

(a) 𝑀_∞=0.3

(b) 𝑀_∞=0.6

(c) 𝑀_∞=0.8

(d) 𝑀_∞=1.0

(e) 𝑀_∞=1.1

(f) 𝑀_∞=1.3