Experimental study on interference flow of a supersonic Busemann biplane
| Autor: | Nagai, Hiroki, Saito, Kenichi, Ogawa, Toshihiro, Asai, Keisuke |
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| Jazyk: | japonština |
| Rok vydání: | 2008 |
| Předmět: | |
| Zdroj: | 宇宙航空研究開発機構特別資料: 第39回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2007論文集 = JAXA Special Publication: Proceedings of 39th Fluid Dynamics Conference/Aerospace Numerical Simulation Symposium 2007. :22-27 |
| ISSN: | 1349-113X |
| Popis: | An interest in Busemann biplane has been revived and the feasibility of the supersonic biplane is now under investigation by many researchers. However, these studies are based mainly on CFD (Computational Fluid Dynamics) calculations and not validated by experiment so that a discussion on the wave cancellation mechanism between the two wings is very limited. The objective of this research is to measure the wing surface pressure distribution on a Busemann biplane and to study the two-dimensional interference phenomenon between the two wings. Since the Busemann biplane wings are so thin (the wing thickness ratio is 0.05) that it is difficult to install static pressure taps on the model. In this experiment, we used Pressure-Sensitive Paint (PSP) to measure surface pressure distributions on the model. PSP is an optical pressure measurement technique based on photochemical reaction called 'oxygen quenching'. This is a coating type sensor and considered only means to measure pressure fields on a thin airfoil model. In this study, wind tunnel experiment was conducted in a 60 mm x 60 mm indraft supersonic wind tunnel. The surface pressure distribution obtained using PSP were compared with CFD results and the Schlieren images. The complicated three-dimensional interference phenomenon between the two wings, including shock wave/boundary layer interactions was analyzed. On the basis of these experimental results, the wave cancellation mechanism of the Busemann biplane is discussed. 資料番号: AA0063742004 レポート番号: JAXA-SP-07-016 |
| Databáze: | OpenAIRE |
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