@article{oai:jaxa.repo.nii.ac.jp:00034406,
 author = {KARASHIMA, Keiichi and KUBOTA, Hirotoshi and SATO, Kiyoshi},
 issue = {7},
 journal = {ISAS report/Institute of Space and Aeronautical Science,University of Tokyo},
 month = {Jun},
 note = {A theoretical approach to aerodynamic mechanism of ablation is made for the region downstream of stagnation point of blunt-nosed axially symmetric bodies at hypersonic speeds on the basis of small perturbation approximation. Fundamental equations are derived, under an assumption of sublimating ablation, for a non-reacting laminar boundary layer flow of binary gas mixture, in which transport properties are taken exactly into consideration by use of atomic kinetic theory of gases. It is shown that all physical properties concerning the ablative field can be uniquely determined by matching of an aerodynamic solution with a static one obtained from chemical kinetics. An emphasis is laid on the fact that perturbation field has no longer similar solutions, while basic field has similar ones for given perimetric conditions. Numerical calculation carried out for teflon ablator indicates that local ablation rate decreases gradually with increase of distance from stagnation point and the ratio of local ablation to stagnation ablation rate tends to increase with increase of stagnation temperature in free stream. In order to confirm validity of the present approach, theoretical results are compared with experimental data for teflon. Agreement between theory and experiment is fairly good near the region of stagnation point at free stream stagnation temperature near 1200℃., 資料番号: SA2400594000},
 pages = {157--191},
 title = {An Aerodynamic Study of Ablation Near the Region of Stagnation Point of Axially Symmetric Bodies at Hypersonic Speeds},
 volume = {33},
 year = {1968}
}