A Study on Numerical Method for Evaluating Spanwise Integral in Subsonic Lifting-Surface Theory

Material type: 文書・図像類

Author: 市川, 輝雄ほか

Publisher: 航空宇宙技術研究所

Publication date: 1981-03

Material Format: Digital

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Note (General)：: NLRの方法の翼幅方向積分における二つの問題点について考察した.第1の問題点は各標点断面が翼幅方向積分点の一つと一致することである.このため,この一致した点での正則化した影響関数の値を計算する必要があり,定常翼の場合を除いてこれは多大の計算時間を消費する.第2の問題点は正則化した影響関数が標点断面の...

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Material Type: 文書・図像類
Title: A Study on Numerical Method for Evaluating Spanwise Integral in Subsonic Lifting-Surface Theory
Author/Editor: 市川, 輝雄
ICHIKAWA, Teruo
Author Heading: 市川, 輝雄
ICHIKAWA, Teruo
Publication, Distribution, etc.: 航空宇宙技術研究所
Publication Date: 1981-03
Publication Date (W3CDTF): 1981-03
Periodical title: Technical Report of National Aerospace Laboratory TR-661T
No. or year of volume/issue: 661T
Volume: 661T
Pages: 13-
ISSN (Periodical Title): ISSN : 0389-4010
Text Language Code: eng
Target Audience: 一般
Note (General): NLRの方法の翼幅方向積分における二つの問題点について考察した.第1の問題点は各標点断面が翼幅方向積分点の一つと一致することである.このため,この一致した点での正則化した影響関数の値を計算する必要があり,定常翼の場合を除いてこれは多大の計算時間を消費する.第2の問題点は正則化した影響関数が標点断面の近くで比較的小さいが望ましくない急激な変化をすることで,この事が翼幅方向積分点を多く取らなければならない原因となっている.これらの困難を解決する改善策として方法1と方法2を提案し,その効果を調べるため,簡単な形の空力荷重分布を持つ定常短形翼の翼面上の吹下ろしを計算した.方法1は上記の一致を避ける方法で,これによって振動翼の場合に精度を損なわずに計算時間を大幅に減らし得ることがわかった.また方法2は翼幅方向積分点を標点断面の付近でだけ密にする方法で,これによって吹下ろしの翼幅方向積分点数に関する収束性が著しく改善されることがわかった.
Two disputable points in the spanwise integral in the NLR method are discussed. The first point is the coincidence of each collocation section with one of the spanwise integration points. This makes necessary the evaluation of the regularized functions at the coincident points, which is very time consuming except in cases of steady wings. The second point is the relatively small, but undesirable, sharp variation of the regularized influence functions near the collocation sections, which is the cause of the necessity of taking a large number of spanwise integration points. Two proposals for coping with these difficulties are made. We call these proposals Method 1 and Method 2. Their effects are examined by computing the downwash at the surface of a steady rectangular wing subjected to a simple wing loading. It is shown that Method 1, which avoids the coincidence, makes it possible, with no losses in accuracy, to greatly reduce the computing time in cases of oscillating wings. Further, it is shown that remarkable improvement in convergence with repect to the number of spanwise integration points is obtained by Method 2 which distributes the spanwise integration points densely only near the collocation sections.
資料番号: NALTR0661000
レポート番号: NAL TR-661T
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