摘要: A transonic wind tunnel test of an 8% F/A-18E model was conducted in the NASA Langley Research Center (LaRC) 16 ft Transonic Tunnel (16-ft TT) to investigate on-surface flow physics during stall. The technical approach employed fo... 展开
作者 | McMillin, S. N. Hall, R. M. Lamar, J. E. | ||
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原报告号 | N20030012596 | 总页数 | 40 |
报告类别/文献类型 | NASA / NTIS科技报告 | ||
关键词 | Wind tunnel tests Transonic wind tunnels Aerodynamic stalling F-18 aircraft Wings Unsteady aerodynamics Pressure measurement Mean square values Wind tunnel models Angle of attack Wing panels Bending moments Pressure sensitive paints Time measurement Trailing edges Unsteady flow |