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International Journal of Aerospace Engineering
Volume 2013, Article ID 231434, 10 pages
Research Article

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

1Institute of Fluid Science, Tohoku University, Sendai 980-8577, Japan
2Institut für Physik der Atmosphäre, Deutsches Zentrum für Luft- und Raumfahrt, 82234 Oberpfaffenhofen, Germany
3Honda R&D Co., Ltd., Haga 321-3321, Japan
4Department of Aerospace Engineering, Tohoku University, Sendai 980-8579, Japan

Received 17 July 2013; Accepted 20 September 2013

Academic Editor: James J. McGuirk

Copyright © 2013 Hiroshi Yamashita et al. This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.


This study describes the start/unstart characteristics of a finite and rectangular supersonic biplane wing. Two wing models were tested in wind tunnels with aspect ratios of 0.75 (model A) and 2.5 (model B). The models were composed of a Busemann biplane section. The tests were carried out using supersonic and transonic wind tunnels over a Mach number range of with angles of attack of 0°, 2°, and 4°. The Schlieren system was used to observe the flow characteristics around the models. The experimental results showed that these models had start/unstart characteristics that differed from those of the Busemann biplane (two dimensional) owing to three-dimensional effects. Models A and B started at lower Mach numbers than the Busemann biplane. The characteristics also varied with aspect ratio: model A () started at a lower Mach number than model B () owing to the lower aspect ratio. Model B was located in the double solution domain for the start/unstart characteristics at , and model B was in either the start or unstart state at . Once the state was determined, either state was stable.