Normal Force Coefficient of Supersonic Flows over Conical Flare, Cone-cylinder and Conical Boattails

Material type: 文書・図像類

Author: 野溝, 国生ほか

Publisher: 航空宇宙技術研究所

Publication date: 1987-10

Material Format: Digital

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Note (General)：: A numerical calculation of the supersonic flow of a perfect gas over conical flares, cone-cylindar and conical boattail at a small angle of attack was...

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Material Type: 文書・図像類
Title: Normal Force Coefficient of Supersonic Flows over Conical Flare, Cone-cylinder and Conical Boattails
Author/Editor: 野溝, 国生
NOMIZO, Kunio
Author Heading: 野溝, 国生
NOMIZO, Kunio
Publication, Distribution, etc.: 航空宇宙技術研究所
Publication Date: 1987-10
Publication Date (W3CDTF): 1987-10
Alternative Title: 超音速三次元流に対する特性曲線法について
Periodical title: 航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-949
No. or year of volume/issue: 949
Volume: 949
Pages: 19-
ISSN (Periodical Title): ISSN : 0389-4010
Text Language Code: eng
Target Audience: 一般
Note (General): A numerical calculation of the supersonic flow of a perfect gas over conical flares, cone-cylindar and conical boattail at a small angle of attack was performed. The Allen. E. PUCKETT method was found to be useful for predicting the flow field about conical Flares with slope abnormalities. The relationship of the normal force distribution between linearized theory and the present method is shown. The normal force distribution calculated by the present method was found to be smaller than that of linearized theory as a whole. Linearized theory estimates the density of gas to be thicker than that of present theory. The present method was simplified by eliminating the density terms. According to the linearized theory, the normal force coefficient is determined by the area ratio of a flare or boattail and is constant along the flare or boattail surface. However, the present method shows that the normal force coefficient decreased downstream, since the density of a gas decreases as it flows downstream. Even if the mach number varies, linearized theory shows that normal force is constant. But present theory shows that normal force decreases as mach number increases for flare and boattails and exact analytical solution is obtained for supersonic flow along with a slighly inclined circular cone. The governing equations are simplified by eliminating the desity terms, and the after-body of a cone cylinder was calculated by the present method. In the present paper, we also investigate overexpanded sonic jets through axisymetric conical nozzles and investigated the effect of pressure and mach number of super sonic jets.
資料番号: NALTR0949000
レポート番号: NAL TR-949
Access Restrictions: 限定公開
Data Provider (Database): 国立情報学研究所 : 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）
https://irdb.nii.ac.jp
Original Data Provider (Database): 宇宙航空研究開発機構 : 宇宙航空研究開発機構リポジトリ