大型衝撃風洞の新運転手法

• Material Type: 文書・図像類
• Title: 大型衝撃風洞の新運転手法
• Author/Editor: 曽我, 国男; 井上, 安敏; 山崎, 喬; SOGA, Kunio; INOUE, Yasutoshi; YAMAZAKI, Takashi
• Author Heading: 曽我, 国男; 井上, 安敏; 山崎, 喬; SOGA, Kunio; INOUE, Yasutoshi; YAMAZAKI, Takashi
• Publication, Distribution, etc.: 航空宇宙技術研究所
• Publication Date: 1983-06
• Publication Date (W3CDTF): 1983-06
• Alternative Title: A New Operation Method for a Large-Scale Shock Tunnel
• Periodical title: 航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-765
• No. or year of volume/issue: 765
• Volume: 765
• Pages: 12-
• ISSN (Periodical Title): ISSN : 0389-4010
• Text Language Code: jpn
• Target Audience: 一般
• Note (General): In order to construct and operate a large-scale shock tunnel for use in such projects as the recovery of rocket payloads and artificial satellites, a new operational method for short-duration wind tunnels using a large-orifice plate and high speed valves is proposed in this paper. The practicability of this method has been studied using the tunnel, and the results of these experiments are shown in this paper. The subject matter of the experimental study was the measurements of the tunnel stagnation pressure and temperature changing the orifice area with and without a piston; performance test of the high speed valve installed in front of the nozzle; and measurements of pitot pressure and stagnation heat-transfer rate of the cylinder to diagnose the flow established in the test section. The results of the preliminary experiment showed that the present method would be very useful for construction and operation of a large-scale short duration wind tunnel. The exclusion of the diaphragms and the piston enabled us not only to make a large-scale wind tunnel but also to eliminate dust in the flow. By using a large-orifice plate together with high speed valves, early stabilization of tunnel stagnation conditions and a steady flow in the test section were achieved. The use of high speed valves to replace the diaphragms and the elimination of the piston enabled us to reuse both the states of high pressure in the driver tube and the partially evacuated pressure in the dump tank after the tunnel operation. Therefore, the tunnel reset time was reduced dramatically. The effect of a piston on the performance of the tunnel was negligible. On the basis of the above results, a construction plan for a large-scale shock tunnel to do research on a hypersonic flow having Mach numbers of 10 and 15 is presented. The tunnel consists of a spherical high pressure chamber of 10m3 which can withstand air pressure of 30M Pa, an electrically heated driven tube 25cm in diameter and 20.5m in length and two spherical vacuum chambers of 1,800m3. The nozzle exit diameter is 60cm.; 資料番号: NALTR0765000; レポート番号: NAL TR-765
• Source: https://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=45023&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