@article{oai:jaxa.repo.nii.ac.jp:00032030,
 author = {辛島, 桂一 and 佐藤, 清 and 久保田, 弘敏 and KARASHIMA, Keiichi and SATO, Kiyoshi and KUBOTA, Hirotoshi},
 issue = {3_A},
 journal = {東京大学宇宙航空研究所報告},
 month = {Jul},
 note = {軸対称鈍頭物体のよどみ点近傍における局所ablation rateの測定結果の報告である.実験に使われた模型は,テフロンで作った数種の曲率半径をもつ半球で,光学的方法によって直接に局所ablation rateを測定する.よどみ点ablation rateとの比は下流方向へ単調減少しており,これは,物体頭部の曲率半径と主流よどみ点温度に関係している.主流よどみ点温度1100℃以上では,軸対称鈍頭物体のよどみ点近傍の実験結果と第一次近似理論との一致はかなり良好である., Present paper gives the results of experimental measurement of local ablation rate near the region of stagnation point of blunt-nosed axially symmetric bodies at hypersonic speeds. The models used in the experiment are hemispherecylinders with various nose-radius of curvature made of teflon and the measurement of local ablation rate is made directly by use of an optical method. It is shown that the ratio of local to stagnaiton ablation rates decreases menotonously onto downstream, depending upon the nose-radius of curvature and stagnation temperature in free stream. Comparison of the experimental results with a first-order approximate theory indicates that the agreement is fairly good near the region of stagnation point at stagnation temperature in free stream beyond 1100℃., 資料番号: SA0125120000},
 pages = {335--347},
 title = {極超音速軸対称鈍頭物体のよどみ点近傍におけるアブレーションの実験的研究},
 volume = {4},
 year = {1968}
}