Mach Number Calibration of 0.44 m Hypersonic Shock Tunnel with a Turntable Model Support System

  • YAMAZAKI Takashi
    Hypersonic Wind Tunnel Section, Wind Tunnel Technology Center, Institute of Space Technology and Aeronautics
  • NAKAKITA Kazuyuki
    Hypersonic Wind Tunnel Section, Wind Tunnel Technology Center, Institute of Space Technology and Aeronautics
  • SEKINE Hideo
    Hypersonic Wind Tunnel Section, Wind Tunnel Technology Center, Institute of Space Technology and Aeronautics
  • WATARI Minoru
    Hypersonic Wind Tunnel Section, Wind Tunnel Technology Center, Institute of Space Technology and Aeronautics

Bibliographic Information

Other Title
  • 0.44 m 極超音速衝撃風洞ターンテーブル型模型支持装置環境下でのマッハ数校正試験

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Description

Mach number calibration tests were conducted at the JAXA 0.44 m Hypersonic Shock Tunnel. Mach number distributions were deduced from the measurements of Pitot pressures and the stagnation pressure, and the estimated stagnation temperature. Pitot pressures were measured by a Pitot rake equipped with 23 ports. From the Pitot pressure distribution, the uniform core was defined as 0.21 m in diameter and 0.30 m in length. Average Mach numbers were 9.79〜10.43 depending on the initial pressures of the high pressure tube and the low pressure tube. Estimated uncertainties in the Mach numbers of the uniform core region were ±0.17.

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Details 詳細情報について

  • CRID
    1574231877040442240
  • NII Article ID
    110006207672
  • NII Book ID
    AA1192675X
  • ISSN
    13491113
  • Text Lang
    ja
  • Data Source
    • CiNii Articles

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