超・亜両側からの古典的音速理論(線型)の若干の数値計算

Material type: 文書・図像類

Author: 山本, 雄三ほか

Publisher: 航空宇宙技術研究所

Publication date: 1985-11

Material Format: Digital

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Note (General)：: In this paper, unsteady aerodynamics of a two-dimensional wing at sonic speed are studied by using so-called classical sonic theories (linear), approa...

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Material Type: 文書・図像類
Title: 超・亜両側からの古典的音速理論(線型)の若干の数値計算
Author/Editor: 山本, 雄三
安東, 茂典
Yamamoto, Yuzo
Ando, Shigenori
Author Heading: 山本, 雄三
安東, 茂典
Yamamoto, Yuzo
Ando, Shigenori
Publication, Distribution, etc.: 航空宇宙技術研究所
Publication Date: 1985-11
Publication Date (W3CDTF): 1985-11
Alternative Title: Some Numerical Calculations by Using Linear Classical Sonic Theories Approached from Sub- or Supersonic Speeds
Periodical title: 航空宇宙技術研究所特別資料 = Special Publication of National Aerospace Laboratory SP-5
No. or year of volume/issue: 5
Volume: 5
Pages: 121-130
ISSN (Periodical Title): ISSN : 0289-260X
Text Language Code: jpn
Target Audience: 一般
Note (General): In this paper, unsteady aerodynamics of a two-dimensional wing at sonic speed are studied by using so-called classical sonic theories (linear), approached from supersonic flow (M
In this paper, unsteady aerodynamics of a two-dimensional wing at sonic speed are studied by using so-called classical sonic theories (linear), approached from supersonic flow (M = 1 + 0) or subsonic flow (M = 1 - 0). In the former approach, the exact expressions of lift and lift distribution are obtained in terms of Fresnel integrals, while in the latter approach an integral equation must bc solved, the kernel function of which is obtained from the subsonic Possio's equation and has a root singularity. The discrete analysis is adopted on the basis of the semi-circle method (SCM) and the weighting function for subsonic-flow-Gauss'-quadrature, as well as modified diagonal elements resulting from the root singularity. Aerodynamic characteristics obtained from both approaches agree quite well with each other. The results obtained by the present computations are compared with those of DLM-C (subsonic 2D code) developed by ANDO et al, and are found to give a reasonable outer boundary for subsonic unsteady aerodynamics.
資料番号: NALSP0005016
レポート番号: NAL SP-5
Access Restrictions: 限定公開
Periodical Title (NCID): AN10097345
https://ci.nii.ac.jp/ncid/AN10097345
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