@inproceedings{oai:jaxa.repo.nii.ac.jp:00004262,
 author = {佐藤, 博紀 and Sato, Hiroki},
 book = {宇宙航空研究開発機構特別資料, JAXA Special Publication: Proceedings of 44th Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2012},
 month = {Mar},
 note = {第44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2012 (2012年7月5日-6日. 富山国際会議場大手町フォーラム), 富山市, 富山県, 44th Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2012 (July 5-6, 2012. Toyama International Conference Center), Toyama Japan, We aim to reveal the generated process of rocket clouds around the rocket fairing in the condensing flow and investigate the aerodynamic characteristics of the fairing. In this study, a two-dimensional or axisymmetrical two-dimensional CFD code considering the heterogenous condensation was developed. Then, the dry air and the heterogenous condensing flow within the circular-arc bump channel (Minf = 0.675, Tinf = 300 K, Pinf = 1000 hPa) and around the rocket fairing (simulated 4S-type for H-IIA, Minf = 0.85, Tinf = 300 K, Pinf = 1000 hPa) were solved by developed code. In the case of the dry air flow in circular-arc bump channel, the results of the present study is in good agreement with that of the past validated numerical study. Compared to the dry air flow, the shock position on the circular-arc bump is shifted to downstream in the heterogenous condensing flow. This trend is in agreement with the past numerical simulation. In the case of the"""  heterogenous condensing flow around the rocket fairing, the temperature, the relative humidity and the mass fraction of the liquid phase are 268 K, 314% and 1.1% respectively at the shoulder of the fairing z = 66.1 m (the fairing tip is located at z = 60 m). The rocket clouds like umbrella is generated near the z = 66.1 m. Compared to the case of the dry air flow, the shock position on the rocket fairing wall is shifted to downstream in the case of the heterogenous condensing flow. This reason can be explained by the comparison between the Rankine-Hugoniot relation and the Rayleigh relation. In addition, the maximum Mach number in the heterogenous condensing flow is lower than that in the dry flow. The difference of the static pressure between the dry air and the heterogenous condensing flow is observed on the side wall of the fairing from z = 66.1 m to 68.5 m., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA0061958022, レポート番号: JAXA-SP-12-010},
 pages = {133--138},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {ロケットフェアリング周りの凝縮流れの数値計算},
 volume = {JAXA-SP-12-010},
 year = {2013}
}