Comparative force/heat flux measurements between JAXA hypersonic test facilities using standard model HB-2

• Material Type: 文書・図像類
• Title: Comparative force/heat flux measurements between JAXA hypersonic test facilities using standard model HB-2
• Author/Editor: 口石, 茂; 渡辺, 重哉; 植田, 修一; 丹野, 英幸; 小室, 智幸; 佐藤, 和雄; 伊藤, 勝宏; Kuchiishi, Shigeru; Watanabe, Shigeya; Ueda, Shuichi; Tanno, Hideyuki; Komuro, Tomoyuki; Sato, Kazuo; Ito, Katsuhiro
• Author Heading: 口石, 茂; 渡辺, 重哉; 植田, 修一; 丹野, 英幸; 小室, 智幸; 佐藤, 和雄; 伊藤, 勝宏; Kuchiishi, Shigeru; Watanabe, Shigeya; Ueda, Shuichi; Tanno, Hideyuki; Komuro, Tomoyuki; Sato, Kazuo; Ito, Katsuhiro
• Publication, Distribution, etc.: 宇宙航空研究開発機構
• Publication Date: 2006-03-31
• Publication Date (W3CDTF): 2006-03-31
• Alternative Title: High enthalpy shock tunnel results
• Periodical title: 宇宙航空研究開発機構研究開発報告 = JAXA Research and Development Report
• No. or year of volume/issue: JAXA-RR-05-030E
• Volume: JAXA-RR-05-030E
• ISSN (Periodical Title): ISSN : 1349-1113
• Text Language Code: eng
• Subject Heading: 比較; 測定装置; 力の測定; 熱流束測定; 高エンタルピ衝撃風洞; 風洞模型; 空気力; 空力加熱; 極超音速風洞; comparison; measuring instrument; force measurement; heat flux measurement; high enthalpy shock tunnel; wind tunnel model; aerodynamic force; aerodynamic heating; hypersonic wind tunnel
• Target Audience: 一般
• Note (General): 本報告は、JAXA高エンタルピ衝撃風洞(HIEST)において実施された、HB-2形状バリスティック標準模型を用いた空気力/空力加熱率測定試験結果に関するものである。力試験はアルミ製模型に十字1列型3分力天秤を装着して実施され、データの振動成分を除去するために加速度補正が施された。熱試験で用いられた模型はクロメル製で計28個の同軸熱電対が装着されてあり、温度時間履歴データを1次元熱伝導の仮定の下で数値的に積分することにより加熱率を求めた。力/熱試験共にコニカルノズルを使用し、力試験についてはエンタルピ4、8、11MJ/kg、熱試験については4、8MJ/kgの試験条件でそれぞれ実施された。力試験結果はエンタルピ4MJ/kg条件の場合、軸力係数に関して他風洞の試験データと良好な傾向の一致を示している一方で、8、11MJ/kgの場合は系統的なずれが観測されており、実在気体効果の影響が可能性として示唆される。一方熱試験における無次元加熱率データは、ブローダウン式コールド極超音速風洞データと模型頭部において数％程度の範囲でよい一致を示した。本試験は、JAXA極超音速関連風洞対応風試の一環として実施されたものであり、また本試験データは高エンタルピ衝撃風洞における基礎データとしても有用である。; This report presents a detailed description and results of force and heat flux measurements conducted at the High-Enthalpy Shock Tunnel (HIEST) of the Japan Aerospace Exploration Agency (JAXA). The HB-2 standard hypersonic ballistic configuration was employed as a model. The force measurement tests used an aluminum alloy model and a three-component aerodynamic balance. An acceleration compensation technique was used to remove vibration components from the original data. Heat flux measurement tests used a chromel model with a total of 28 co-axial thermocouples press-fitted onto the surface. Time histories of temperature data were numerically integrated to determine the surface heat flux by applying one-dimensional heat conduction theory. Both force and heat tests used a conical nozzle, and a total of three enthalpy levels of 4, 8, and 11 MJ/kg and two levels of 4 and 8 MJ/kg were set for the force and heat tests, respectively. Although much higher stagnation enthalpy can be attained, relatively lower enthalpy levels were selected to compare with a blow-down type hypersonic wind tunnel and to alleviate uncertainties inherent in high-enthalpy facilities. The force test results correlated well with other hypersonic wind-tunnel data for the axial force coefficient at the enthalpy level of 4 MJ/kg, while a notable discrepancy was observed at the higher enthalpy levels of 8 and 11 MJ/kg. The real gas effects on aerodynamic characteristics are examined and discussed. In the heat test, a comparison of the heat flux distribution along the surface with data obtained in a blow-down type hypersonic wind tunnel showed good agreement in the nose part, typically within several percent. The present experiment was conducted as a series of comparative test campaigns between two hypersonic facilities in JAXA. Since the tunnel stagnation conditions and the corresponding data are tabulated in detail for each shot, the present test data are believed to serve as a complete database for evaluating aerodynamic force and heat flux data obtained at large-scale high-enthalpy shock tunnels.; 資料番号: AA0049482000; レポート番号: JAXA-RR-05-030E
• Access Restrictions: 限定公開
• Periodical Title (NCID): AA1192675X; https://ci.nii.ac.jp/ncid/AA1192675X
• 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