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

Figure 14

Regions of influence in supersonic flow on finite biplane wings: (a) model A (AR = 0.75) and (b) model B (AR = 2.5). The illustrations show the upper surface of the lower wing element (plan view). The broken lines indicate the Mach cone generated from each tip at 𝑀_∞=1.5 (𝜇=41.8^∘).

(a) Model A

(b) Model B