Wind Tunnel Testing on Start/Unstart Characteristics of Finite Supersonic Biplane Wing
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 sup...
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| Main Authors: | , , , , , , |
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| Format: | Article |
| Language: | English |
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Wiley
2013-01-01
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| Series: | International Journal of Aerospace Engineering |
| Online Access: | http://dx.doi.org/10.1155/2013/231434 |
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| _version_ | 1832550172296478720 |
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| author | Hiroshi Yamashita Naoshi Kuratani Masahito Yonezawa Toshihiro Ogawa Hiroki Nagai Keisuke Asai Shigeru Obayashi |
| author_facet | Hiroshi Yamashita Naoshi Kuratani Masahito Yonezawa Toshihiro Ogawa Hiroki Nagai Keisuke Asai Shigeru Obayashi |
| author_sort | Hiroshi Yamashita |
| collection | DOAJ |
| description | 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 0.3≤M∞≤2.3 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 (1.3<M∞<1.5) started at a lower Mach number than model B (1.6<M∞<1.8) owing to the lower aspect ratio. Model B was located in the double solution domain for the start/unstart characteristics at M∞=1.7, and model B was in either the start or unstart state at M∞=1.7. Once the state was determined, either state was stable. |
| format | Article |
| id | doaj-art-dbacb799c85842cab73ec707950f2cae |
| institution | Kabale University |
| issn | 1687-5966 1687-5974 |
| language | English |
| publishDate | 2013-01-01 |
| publisher | Wiley |
| record_format | Article |
| series | International Journal of Aerospace Engineering |
| spelling | doaj-art-dbacb799c85842cab73ec707950f2cae2025-02-03T06:07:30ZengWileyInternational Journal of Aerospace Engineering1687-59661687-59742013-01-01201310.1155/2013/231434231434Wind Tunnel Testing on Start/Unstart Characteristics of Finite Supersonic Biplane WingHiroshi Yamashita0Naoshi Kuratani1Masahito Yonezawa2Toshihiro Ogawa3Hiroki Nagai4Keisuke Asai5Shigeru Obayashi6Institute of Fluid Science, Tohoku University, Sendai 980-8577, JapanInstitute of Fluid Science, Tohoku University, Sendai 980-8577, JapanInstitute of Fluid Science, Tohoku University, Sendai 980-8577, JapanInstitute of Fluid Science, Tohoku University, Sendai 980-8577, JapanDepartment of Aerospace Engineering, Tohoku University, Sendai 980-8579, JapanDepartment of Aerospace Engineering, Tohoku University, Sendai 980-8579, JapanInstitute of Fluid Science, Tohoku University, Sendai 980-8577, JapanThis 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 0.3≤M∞≤2.3 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 (1.3<M∞<1.5) started at a lower Mach number than model B (1.6<M∞<1.8) owing to the lower aspect ratio. Model B was located in the double solution domain for the start/unstart characteristics at M∞=1.7, and model B was in either the start or unstart state at M∞=1.7. Once the state was determined, either state was stable.http://dx.doi.org/10.1155/2013/231434 |
| spellingShingle | Hiroshi Yamashita Naoshi Kuratani Masahito Yonezawa Toshihiro Ogawa Hiroki Nagai Keisuke Asai Shigeru Obayashi Wind Tunnel Testing on Start/Unstart Characteristics of Finite Supersonic Biplane Wing International Journal of Aerospace Engineering |
| title | Wind Tunnel Testing on Start/Unstart Characteristics of Finite Supersonic Biplane Wing |
| title_full | Wind Tunnel Testing on Start/Unstart Characteristics of Finite Supersonic Biplane Wing |
| title_fullStr | Wind Tunnel Testing on Start/Unstart Characteristics of Finite Supersonic Biplane Wing |
| title_full_unstemmed | Wind Tunnel Testing on Start/Unstart Characteristics of Finite Supersonic Biplane Wing |
| title_short | Wind Tunnel Testing on Start/Unstart Characteristics of Finite Supersonic Biplane Wing |
| title_sort | wind tunnel testing on start unstart characteristics of finite supersonic biplane wing |
| url | http://dx.doi.org/10.1155/2013/231434 |
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