Japan Aerospace Exploration Agency Wind Tunnel Technology Center, Institute of Space Technology and Aeronautics
Japan Aerospace Exploration Agency Wind Tunnel Technology Center, Institute of Space Technology and Aeronautics
Japan Aerospace Exploration Agency Wind Tunnel Technology Center, Institute of Space Technology and Aeronautics
Japan Aerospace Exploration Agency Wind Tunnel Technology Center, Institute of Space Technology and Aeronautics
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.
0.44m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
49489000.pdf
(4.42MB)
