| Item type |
テクニカルレポート / Technical Report(1) |
| 公開日 |
2015-03-26 |
| タイトル |
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タイトル |
ナビエストークス方程式による二次元翼まわりの遷音速流の数値解析 |
| 言語 |
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言語 |
jpn |
| 資源タイプ |
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資源タイプ識別子 |
http://purl.org/coar/resource_type/c_18gh |
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資源タイプ |
technical report |
| その他のタイトル（英） |
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その他のタイトル |
Numerical Analysis of Transonic Flow around Two-Dimensional Airfoil by Solving Navier-Stokes Equations |
| 著者 |
汪, 翼雲
藤原, 俊隆
Wang, Yi-Yun
Fujiwara, Toshi
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| 著者所属 |
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名古屋大学工学部 |
| 著者所属 |
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名古屋大学工学部 |
| 著者所属（英） |
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en |
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Department of Aeronautical Engineering, Nagoya University |
| 著者所属（英） |
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en |
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Department of Aeronautical Engineering, Nagoya University |
| 出版者 |
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出版者 |
航空宇宙技術研究所 |
| 出版者（英） |
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出版者 |
National Aerospace Laboratory(NAL) |
| 書誌情報 |
航空宇宙技術研究所特別資料
en : Special Publication of National Aerospace Laboratory SP-3
巻 3,
p. 221-228,
発行日 1984-11
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| 抄録（英） |
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内容記述タイプ |
Other |
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内容記述 |
An effective finite-difference scheme for solving full compressible Navier-Stokes equations was initated by Beam and Warming. The purpose of this paper is to develop that technique and apply it to the calculation of a typical subsonic or transonic, inviscid or viscous steady flow. We almost identically follow the Beam-Warming technique that may be summarized into the following threee characteristics: a) Delta-form approximate factorization algorithm, b) Implicit three-level scheme. c) The cross derivative viscous terms were explicitly replaced by the values of previous time. First, the strong conservation-law form of the Navier-Stokes equations is written in Cartesian coordinates, and then transformed into a general grid system. Following the Beam-Warming difference scheme, we generally adopt the parameter combination delta |
| 抄録（英） |
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内容記述タイプ |
Other |
|
内容記述 |
An effective finite-difference scheme for solving full compressible Navier-Stokes equations was initated by Beam and Warming. The purpose of this paper is to develop that technique and apply it to the calculation of a typical subsonic or transonic, inviscid or viscous steady flow. We almost identically follow the Beam-Warming technique that may be summarized into the following threee characteristics: a) Delta-form approximate factorization algorithm, b) Implicit three-level scheme. c) The cross derivative viscous terms were explicitly replaced by the values of previous time. First, the strong conservation-law form of the Navier-Stokes equations is written in Cartesian coordinates, and then transformed into a general grid system. Following the Beam-Warming difference scheme, we generally adopt the parameter combination delta = l/2 and theta = 1. After introducing spatial factorization, second-order dissipative terms are added to the left-hand side, while fourth-order terms are added to the right-hand side; the fourth-order smoothing terms are changed to second-order terms at points adjacent to the boundaries. The numerical computations were carried out only for a typical NACA 0012 airfoil. The grid system used is a C-type, where 51 points are distributed uniformly over the airfoil surface with identical arc length. The lines of constant xi consist of two parts: One part of those emanating from the airfoil sulface points is the solution of the Laplace equation and the others are parabolas. The distribution of points on wake cut and in the eta-direction is exponential. The calculations start from uniform free-stream variables throughout the flow field. The boundary conditions in the far field are free-stream. The following four cases are calculated:a) M infinity =0.63 and alpha=0, causing an entirely subsonic flow. b) M infinity =0.63 and alpha=2 degrees, the highest velocity of upper surface being close to sonic c) M infinity =0.75 and alpha=0, when supersonic regions appear but there are no shock waves. The flow is supercritical. d) M infinity =0.75 and alpha=2 degrees, generating a shock wave over the upper flow field. The flow is transonic in the case of inviscid calculations. Viscous calculations, on the other hand, show no shock waves, while flow separation on the upper surface caused by the angle of attack is conspicuous. |
| ISSN |
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収録物識別子タイプ |
ISSN |
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収録物識別子 |
0289-260X |
| 書誌レコードID |
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収録物識別子タイプ |
NCID |
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収録物識別子 |
AN10097345 |
| 資料番号 |
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内容記述タイプ |
Other |
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内容記述 |
資料番号: NALSP0003027 |
| レポート番号 |
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内容記述タイプ |
Other |
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内容記述 |
レポート番号: NAL SP-3 |
nalsp0003027.pdf (463.5 kB)
