@inproceedings{oai:jaxa.repo.nii.ac.jp:00037328,
 author = {伊藤, 勝宏 and 植田, 修一 and 高橋, 政浩 and 丹野, 英幸 and 小室, 智幸 and 佐藤, 和雄 and Ito, Katsuhiro and Ueda, Shuichi and Takahashi, Masahiro and Tanno, Hideyuki and Komuro, Tomoyuki and Sato, Kazuo},
 book = {航空宇宙技術研究所特別資料, Special Publication of National Aerospace Laboratory},
 month = {Feb},
 note = {航空宇宙技術研究所 24-26 Jun. 1998 東京 日本, National Aerospace Laboratory 24-26 Jun. 1998 Tokyo Japan, 航空宇宙技術研究所では宇宙往還技術試験機(HOPE-X)およびスクラムジェットエンジンの超高速地上試験用に80m長の大型高温衝撃風洞(HIEST)の開発を進めてきた。HIESTの設計は最適作動法に基づいており、4〜7km/secの速度でのHOPE-X再突入軌道に沿って生じる分子解離によって生じる高温ガス効果の再現を行った。これらの試験では、500mmの模型を用いる場合、ノズル貯気層条件は最大25MJ/kgの淀み点エンタルピおよび最大150Mpaの淀み点圧力が必要である。HIESTの構築は1997年の10月に完了し、主に自由ピストンドライバと衝撃波管の作動特性に重点を置いた初期の作動試験は1998年1月末まで行われた。HIESTが稼動可能となってからこれまで80回の動作試験が行われ、駆動気体汚染の計測、ノズル流検定試験、HOPE-X模型周りの力束および熱流束測定を実施した。ここでは、最適作動法における自由ピストンドライバおよび衝撃波管の性能に焦点を合わせた初期の検証試験の結果を示した。さらに、検証試験を進める上で生ずる高温衝撃ノズル流における重大な問題について論じた。, NAL has been proceeding development of an 80 meter long large High Enthalpy Shock Tunnel (HIEST) for hypervelocity ground testing of HOPE-X (H-2 Orbiting Plane Experimental) and the scramjet engine. The design of HIEST was based on the tuned piston operation theory and carried out so as to duplicate the high temperature real gas effect caused mainly by molecular dissociation along the HOPE-X reentry path in the velocity range of 4 - 7 km/sec. For these testing requirements, a stagnation enthalpy of up to 25 MJ/kg and a stagnation pressure of up to 150 Mpa are required at the nozzle reservoir condition when the 500 mm model is used. The construction phase of the HIEST was completed in October 1997 and a series of initial calibrations which mainly concerned with the characteristics of the free piston driver and the shock tube was proceeded until the end of January 1998. Since the HIEST became operational 80 shots have been conducted so far, for the measurements of driver gas contamination, the nozzle flow calibration, the force and heat flux measurements around the HOPE-X model. Here, the initial calibration results are shown by focusing on the performances of the free piston driver and the shock tube with the tuned operation. Moreover, some critical issues of the high enthalpy nozzle flows which were encountered in the further calibration are discussed., 資料番号: AA0001958014, レポート番号: NAL SP-41},
 pages = {89--94},
 publisher = {航空宇宙技術研究所, National Aerospace Laboratory (NAL)},
 title = {高温衝撃風洞HIESTの作動特性},
 volume = {41},
 year = {1999}
}