| Item type |
テクニカルレポート / Technical Report(1) |
| 公開日 |
2015-03-26 |
| タイトル |
|
|
タイトル |
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 |
| 言語 |
|
|
言語 |
jpn |
| 資源タイプ |
|
|
資源タイプ識別子 |
http://purl.org/coar/resource_type/c_18gh |
|
資源タイプ |
technical report |
| その他のタイトル（英） |
|
|
その他のタイトル |
Calculation of Damping Derivatives for Arbitrary 3-Dimensional Bodies Using Newtonian Impact Theory |
| 著者 |
柳沢, 三憲
菊地, 一雄
YANAGISAWA, Mitsunori
KIKUCHI, Kazuo
|
| 出版者 |
|
|
出版者 |
航空宇宙技術研究所 |
| 出版者（英） |
|
|
出版者 |
National Aerospace Laboratory(NAL) |
| 書誌情報 |
航空宇宙技術研究所報告
en : Technical Report of National Aerospace Laboratory TR-722
巻 722,
p. 11,
発行日 1982-08
|
| 抄録（英） |
|
|
内容記述タイプ |
Other |
|
内容記述 |
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. |
| ISSN |
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|
収録物識別子タイプ |
ISSN |
|
収録物識別子 |
0389-4010 |
| 資料番号 |
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|
内容記述タイプ |
Other |
|
内容記述 |
資料番号: NALTR0722000 |
| レポート番号 |
|
|
内容記述タイプ |
Other |
|
内容記述 |
レポート番号: NAL TR-722 |
naltr00722.pdf (958.7 kB)
