Wind Tunnel Technology Center, Aerospace Research and Development Direstorate, Japan Aerospace Exploration Agency (JAXA)
Wind Tunnel Technology Center, Aerospace Research and Development Direstorate, Japan Aerospace Exploration Agency (JAXA)
Wind Tunnel Technology Center, Aerospace Research and Development Direstorate, Japan Aerospace Exploration Agency (JAXA)
Wind Tunnel Technology Center, Aerospace Research and Development Direstorate, Japan Aerospace Exploration Agency (JAXA)
Kawasaki Heavy Industries
The uniform core flow of the JAXA 1 m x 1 m supersonic wind tunnel was defined as the region of 0.6 m x 0.6 m x 1.0 m. In this uniform core flow region, superior Mach number uniformities were achieved with the 2-Dimensional flexible nozzle at Mach numbers from 1.4 to 4.0. Although it is recommended to use in this region, some tunnel users want to do tests out of this region. In order to meet such requirement, the main flow region was determined by the Pitot pressure distribution measurement within the boundary-layer of the tunnel walls. Since the flow in the test section was known to be vertically symmetric and two-dimensional, the measurement was taken place in the vertical direction only from the floor and the horizontal direction from the one side wall at four Mach numbers of 1.4, 2.0, 3.0 and 4.0. From the measurement results, it was determined that the boundary layer thicknesses were from 40mm to 70mm. In addition, the velocity distributions of the boundary layer both on the floor and the side wall showed good agreements with the turbulent boundary layer profiles estimated by the 1/7 power law.
1m×1m超音速風洞測定部の境界層計測
64261000.pdf
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