@techreport{oai:jaxa.repo.nii.ac.jp:00044979,
 author = {柳沢, 三憲 and 菊地, 一雄 and YANAGISAWA, Mitsunori and KIKUCHI, Kazuo},
 month = {Aug},
 note = {In order to calculate the aerodynamic characteristics of arbitrary 3-D bodies at very high Mach numbers, the Newtonian impact theory can be used by automatically determining the boundaries between exposed and shielded portions of the bodies. In the impact theory, the boundaries at a finite angle of attack are expressed as the relation of geometrical functions of body and a main flow direction. The functions of the boundary are more complicated on an ordinary winged body. For the sake of simplicity in the present analysis, it is assumed by Newtonian theory that the presure coefficients in the shielded portions are zero. The boundaries are easily determined by applying the proposed criteria to each panel of body surface. The pressure coefficients of the shielded portions of the body surface are excluded for the summation of the aerodynamic force. The predicted aerodynamic characteristics of a cone, a cone-cylinder, the Gemini type vehicle and the space shuttle are compared with those measured results., 資料番号: NALTR0722000, レポート番号: NAL TR-722},
 title = {ニュートン流理論を用いた三次元物体の動安定微係数の計算},
 year = {1982}
}