Numerical Simulation of Hypersonic Flow Around a Space Plane III Analysis of Aerothermodynamic Heating

Material type: 文書・図像類

Author: 山本, 行光ほか

Publisher: 航空宇宙技術研究所

Publication date: 1989-08

Material Format: Digital

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Note (General)：: 流速分離TVD風上差分法をスペース・プレーンまわりの極超音速空力加熱解析に適用した。基礎方程式は有限体積表示の薄層近似ナビエ・ストークス方程式で,解法はIAF (Implicit Approximate Factorization)法である。計算は主翼後退角の異なる三種類のスペース・プレーン形状につ...

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Material Type: 文書・図像類
Title: Numerical Simulation of Hypersonic Flow Around a Space Plane III Analysis of Aerothermodynamic Heating
Author/Editor: 山本, 行光
YAMAMOTO, Yukimitsu
ARAKAWA, Haruhiko
YOSHIDA, Ryuji
Author Heading: 山本, 行光
YAMAMOTO, Yukimitsu
ARAKAWA, Haruhiko
YOSHIDA, Ryuji
Publication, Distribution, etc.: 航空宇宙技術研究所
Publication Date: 1989-08
Publication Date (W3CDTF): 1989-08
Periodical title: Technical Report of National Aerospace Laboratory TR-1027T
No. or year of volume/issue: 1027T
Volume: 1027T
Pages: 28-
ISSN (Periodical Title): ISSN : 0389-4010
Text Language Code: eng
Target Audience: 一般
Note (General): 流速分離TVD風上差分法をスペース・プレーンまわりの極超音速空力加熱解析に適用した。基礎方程式は有限体積表示の薄層近似ナビエ・ストークス方程式で,解法はIAF (Implicit Approximate Factorization)法である。計算は主翼後退角の異なる三種類のスペース・プレーン形状について,マッハ数7.0,レイノルズ数4.4×10(exp 6)の条件で迎角0度,10度,20度のケースについて行った。本解析では主に主翼前縁に沿う空力加熱分布について詳細に調べ,また主翼端に取付けられたティップ・フィンの効果についても解析を進めた。計算結果は当初の極超音速風洞で行われた空力加熱試験結果と比較し,良好な一致が得られた。本研究は航空宇宙技術研究所と三菱重工との共同研究「宇宙往還輸送機の概念研究」の一環として行われたものである。
The evaluation of hypersonic aerothermodynamic heating along the wing leading edge of the space plane is very important for preliminary aerothermal structual design, because severe local peak heating is caused there by recompression or shock impingement at low angles of attack. In the present numerical simulation, this local peak heating has been analyzed for the three space plane configurations proposed by the National Aerospace Laboratory(NAL). The proposed models have different wing leading edge sweep angles, and effects of the sweep angles on local peak heating were investigated in detail. In addition, two of the proposed configurations have tip fin controllers, and their heating characteristics were also investigated. As the numerical approach, a flux split upwind TVD scheme has been adopted by using thin layer Navier-Stokes equations in a finite volume formulation. An implicit approximately factored ADI method has been used as the solution algorithm. Numerical computations were carried out at M∞=7.0 and Reynolds number of 4.4×10(exp 6) at angles of attack α=0,10 and 20 deg. Numerical results are compared with experimental heat transfer measurements by the infrared system developed in the hypersonic wind tunnel (HWT)at NAL.
資料番号: NALTR1027000
レポート番号: NAL TR-1027T
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