@inproceedings{oai:jaxa.repo.nii.ac.jp:00005420,
 author = {今村, 宰 and 綿貫, 忠晴 and 鈴木, 宏二郎 and Imamura, Osamu and Rathakrishnan, E. and Watanuki, Tadaharu and Suzuki, Kojiro},
 book = {宇宙航空研究開発機構特別資料: 第40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2008論文集, JAXA Special Publication: Proceedings fo 40th Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2008},
 month = {Feb},
 note = {第40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2008. 会期: 2008年6月12日-6月13日. 会場: 東北大学片平キャンパス, Bleeding blunt nose model is proposed in order to control the aerodynamic characteristics in hypersonic region. The air is bled from the top of the model and it exhausts to the base. The increase in the base pressure is expected and, as a result, the reduction of drag force is expected. This paper reports the experimental results of hemisphere model with different bleed holes in hypersonic wind tunnel and the effect of the bleed hole diameter is discussed. The experiments are performed in a hypersonic wind tunnel, University of Tokyo, in Kashiwa. This wind tunnel enables the Mach number 7 flow of 120 mm in diameter for 60 seconds. In this study, the stagnation pressure is 950 kPa, stagnation temperature is around 600 K and Reynolds number is 1.6 x 10(exp 5), respectively. The prototype model is a hemisphere in 40 mm diameter with a bleeding hole in 5 mm and 10 mm diameter. From the shadowgraph images, the shock distance becomes shorter with the increase of the bleed hole diameter and the shock wave shape becomes concave at the center for larger bleed hole diameter. From the measurement of balance system, drag force coefficient reduces with the increase in the bleed hole diameter and the maximum reduction of drag force coefficient is 10 % of that without bleeding. The main reason for the reduction of drag force is estimated to be increase of the base pressure from the measurement result of base pressure. The base pressure increases with the increase of the bleed hole diameter., 形態: カラー図版あり, 資料番号: AA0064303018, レポート番号: JAXA-SP-08-009},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {抽気孔径が半球模型の極超音速空力特性に及ぼす影響},
 volume = {JAXA-SP-08-009},
 year = {2009}
}