@techreport{oai:jaxa.repo.nii.ac.jp:00044750,
 author = {井上, 安敏 and INOUE, Yasutoshi and Robert, H.Page},
 month = {Apr},
 note = {Base heat transfer of a two-dimensional bluff body in supersonic and hypersonic flows is analysed by the component analysis method, paying special attention to the effect of the approaching turbulent boundary layer thickness on the heat transfer rate. Turbulent mixing between the quiescent fluid in the wake and adjacent isentropic supersonic flow under constant pressure is assumed. Hill’s orgin shift method for the mixing layer is employed in order to deal with the finite thickness effect of the turbulent boundary layer. Heat transfer from the uniform flow to the base wall is analysed by taking account of two resistive elements:(1)heat transfer across the mixing layer, and (2)heat transfer between the recirculating flow and the base wall. The Prandtl number of the turbulent flow is assumed to be unity, and radiation is neglected. The base heat transfer rate is given in terms of the ratio of the boundary layer thickness to the base half-height, wall temperature ratio, and Mach number, stagnation pressure and stagnation temperature of an approaching uniform flow. Variations in the base heat transfer rate versus Mach number, wall temperature and boundary layer momentum thickness ratio are shown and compared with a certain available experimental data. The heat transfer rate shows the initial rapid increase and subsequent tendency to level-off with the increase in boundary layer thickness. Effects of boundary layer thickness on base pressure ratio and wake angle are also discussed., 資料番号: NALTR0497000, レポート番号: NAL TR-497},
 title = {超音速乱流底面熱伝達の一近似解法-境界層厚さを考慮した場合-},
 year = {1977}
}