@techreport{oai:jaxa.repo.nii.ac.jp:00002229,
 author = {関根, 英夫 and 津田, 尚一 and 平林, 則明 and 小山, 忠勇 and 永井, 伸治 and 渡利, 實 and Sekine, Hideo and Tsuda, Shoichi and Hirabayashi, Noriaki and Koyama, Tadao and Nagai, Shinji and Watari, Minoru},
 month = {Mar},
 note = {1.27m極超音速風洞の気流品質確認の一環としてマッハ数校正試験と並行して気流傾角分布測定試験を1999年6月から2000年7月にかけて実施した。表面4点に圧力孔を有し、差圧を検出することで縦横の気流傾角を同時に測定できる円錐プローブ7個を持つ気流傾角レークを適用して試験を効率的に行った。風洞よどみ点温度は800度Cとし、風洞よどみ点圧力は2.5MPa、4MPa、6MPaの3点で試験を実施した。測定範囲については、水平面および鉛直面分布は風洞軸を中心とする幅0.72mをノズル出口から下流0.9mまでを、気流断面分布は風洞軸を中心とする幅0.72m×高さ0.6mを気流方向3箇所で測定した。試験は、気流傾角プローブの校正、傾角プローブ支持部熱変形補正量の取得を行った後、気流傾角分布測定を行った。その結果、風洞中心軸上では、平均して0.05度程度の右下から吹き上がりぎみの気流傾角を持ち、一様流コア全域の気流傾角は最大絶対値で0.2度、平均値で±0.02度以内、95％不確かさ値は±0.13〜0.20度程度であることがわかった。高圧高温配管の熱膨張による気流方向の変動は微小であった。, A series of wind tunnel tests were conducted from June 1999 to July 2000 in the JAXA 1.27 m hypersonic wind tunnel to measure flow angle distribution in the core region. To measure the flow angle, a rake equipped with seven cone-shape probes was used. The probes, which has four circumferentially, equally spaced pressure orifices on the surface, are able to measure flow angles in the vertical and horizontal planes simultaneously. The tests were conducted at a stagnation temperature of 800 C and stagnation pressures of 2.5, 4, and 6 MPa. First, sensitivities for the probe sensors and the deformation effect on the rake caused by aerodynamic heating were investigated. Then, flow distributions were obtained on the horizontal and vertical planes, 0.72 m wide and 0.9 m in length. Cross-sectional distributions 0.72 m wide and 0.6 m high were obtained at three stream-wise positions. The average flow angle in the core region is less than 0.02 degrees and the uncertainty with a 95 percent confidence level is 0.13-0.2 degrees. Effect on the flow angle variation by extension of the high-pressure-high-temperature tube was not significant., 資料番号: AA0063453000, レポート番号: JAXA-RR-06-006},
 title = {1.27m極超音速風洞の気流傾角分布試験},
 year = {2007}
}