A Numerical Simulation of a New Operation Method for Shock Tunnels

Material type: 文書・図像類

Author: 白水, 正男ほか

Publisher: 航空宇宙技術研究所

Publication date: 1988-08

Material Format: Digital

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Note (General)：: The new operation method for shock tunnels which was proposed and verified experimentally by Soga et al.provides a much longer flow duration than that...

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Material Type: 文書・図像類
Title: A Numerical Simulation of a New Operation Method for Shock Tunnels
Author/Editor: 白水, 正男
SHIROUZU, Masao
Author Heading: 白水, 正男
SHIROUZU, Masao
Publication, Distribution, etc.: 航空宇宙技術研究所
Publication Date: 1988-08
Publication Date (W3CDTF): 1988-08
Alternative Title: 新運転手法による衝撃風洞の計算機シミュレーション
Periodical title: 航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-993
No. or year of volume/issue: 993
Volume: 993
Pages: 20-
ISSN (Periodical Title): ISSN : 0389-4010
Text Language Code: eng
Target Audience: 一般
Note (General): The new operation method for shock tunnels which was proposed and verified experimentally by Soga et al.provides a much longer flow duration than that obtained by conventional operation methods. The new operation method employs an orifice plate between the driver and driven sections in order to modify the pressure history at the end of the driven section (i.e.stagnation condition for the nozzle flow) so that the pressure may stabilize much earlier than when an orifice plate is not used. In this new operation method, the first and the second diaphragms are replaced by high-speed valves. The second high-speed valve is kept closed until the pressure is stabilized. Although the effectiveness of the new method was verified experimentally, a technique for predicting the characteristics of facilities was necessary in order to choose the operation parameters for the Middle-Scale Shock Tunnel and to modify the tunnel. Numerical simulations of the flow in the shock tunnel under the new operation method were made emplying the PLM (Piecewise Linear Method). The flow was calculated two-dimensionally in the region near the orifice and one-dimensional flow was assumed in other regions. The simulated pressure history agreed well with the experimental results under various opening area ratios of the orifice. A method was proposed to reduce disturbance in the stagnation pressure caused by the rarefaction wave in the driver section and its effect was verified experimentally. As an example of the application of this simulation technique, the optimal opening ratio of the orifice for a pre-heated shock tunnel is provided. Modification of the NAL Gun Tunnel to change it to this type of tunnel is under way. Some guiding principles for the optimal design of a shock tunnel using the new operation method are given based on the present simulation.
資料番号: NALTR0993000
レポート番号: NAL TR-993
Source: https://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=45252&item_no=1&attribute_id=31&file_no=1
https://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=45252&item_no=1&attribute_id=31&file_no=1
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