This study describes the start/unstart characteristics of a finite and rectangular supersonic biplane wing. Two wing models were\r\ntested in wind tunnels with aspect ratios of 0.75 (model A) and 2.5 (model B). The models were composed of a Busemann biplane\r\nsection. The tests were carried out using supersonic and transonic wind tunnels over a Mach number range of 0.3 = ??8 = 2.3\r\nwith angles of attack of 0�°, 2�°, and 4�°. The Schlieren system was used to observe the flow characteristics around the models. The\r\nexperimental results showed that these models had start/unstart characteristics that differed from those of the Busemann biplane\r\n(two dimensional) owing to three-dimensional effects.Models A and B started at lowerMach numbers than the Busemann biplane.\r\nThe characteristics also varied with aspect ratio: model A (1.3 < ??8 < 1.5) started at a lower Mach number than model B\r\n(1.6 < ??8 < 1.8) owing to the lower aspect ratio. Model B was located in the double solution domain for the start/unstart\r\ncharacteristics at??8 = 1.7, and model B was in either the start or unstart state at??8 = 1.7. Once the state was determined, either\r\nstate was stable.
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