@techreport{oai:jaxa.repo.nii.ac.jp:00043535,
 author = {片山, 雅之 and 黒崎, 隆二郎 and 中村, 淑子 and 麻生, 茂 and 熊坂, 和広 and Katayama, Masayuki and Kurosaki, Ryujiro and Nakamura, Yoshiko and Aso, Shigeru and Kumasaka, Kazuhiro},
 month = {Dec},
 note = {Aerodynamic heating analyses have been performed for axisymmetric bodies in the supersonic flow. both experiments using a shock tunnel and the computations corresponding to the experiments are conducted. Heat flux to the bodies such as a hemisphere-cylinder and an ogive-cylinder are measured. Flow conditions are (1) Mach number M infinity = 4.25 (2) Reynolds numbers Re infinity = 2 - 3x105, based on body radius (3) Stagnation temperatures T0 = 500 - 600K (4) Angle of attack alpha = 0 degrees Results of the experiments and the computations are summarized as follows. Heat flux to the hemisphere surface has the maximum value at the stagnation point and decreases smoothly downstream. Also the heat flux to the ogive surface is quite large in the vicinity of the tip and decreases gradually downstream in the case of fully laminar or fully turbulent flow. In the case of the flow including the transition, increase of heat flux caused by the transition of the boundary layer is observed. LU-ADI difference scheme for compressible Navier-Stokes Code has been used for the computations corresponding to the experiments. Computational results show good correlation to the experimental data obtained by the shock tunnel., 資料番号: NALSP0016039, レポート番号: NAL SP-16},
 title = {超音速飛しょう体頭部形状まわりの空力加熱解析},
 year = {1991}
}