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Low Speed Calibration of the NASA Lewis Research Center 8- by 6-Foot Supersonic Wind Tunnel (1995 Test)
| 题名： | Low Speed Calibration of the NASA Lewis Research Center 8- by 6-Foot Supersonic Wind Tunnel (1995 Test) |
| 作者： | Arrington, E. Allen; Gonsalez, Jose C. |
| 关键词： | calibration；supersonic；tunnel；lewis；research；center；nasa；speed；distribution；section |
| 摘要： | A test section calibration of the NASA Lewis Research Center 8- by 6-Foot Supersonic Wind Tunnel was conducted to provide calibration and flow quality data over the low-speed range of the facility. To accommodate customer needs for lower 8- by 6-ft test section Mach number conditions that would overlap the range of the 9- by 15-ft low-speed test section, two new operational modes were used (1) to set Mach numbers as low as 0.25, the facility drive compressor was operated at lower rotational speeds by using only one of the three electric drive motors (2) to set Mach number conditions between 0.01 and 0.09, the air dryer air blowers were used. Expanding the operational range of the 8- by 6-ft test section provided sufficient overlap with the 9- by 15-ft test section Mach number range (0.0 to 0.20). Calibration test data showed that there was good flow quality in terms of total pressure, Mach number, and flow angle distribution within a plane and axial static pressure distribution along the test section centerline. A temperature gradient was re- corded along the outside third of the test section for one-drive-motor operation (temperature surveys were not made during air-blower operation). Calibration curves relating centerline conditions at the model test plane were constructed and have been used successfully in research testing conducted over the low-speed regime. |
| 报告类型： | 科技报告 |
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