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|標題:||Static and Dynamic Aerocharacteristics Testing of Strake-Wing Aerial Vehicle in Water Tunnel||作者:||Chang, L.M.
|關鍵字:||Strake-Wing;High Attack Angle;Sideslip Angle;Pitching;Force/Moment;Vortex Breakdown;speed unsteady aerodynamics;reynolds-number;high angles;attack;model;flow||Project:||Transactions of the Japan Society for Aeronautical and Space Sciences||期刊/報告no：:||Transactions of the Japan Society for Aeronautical and Space Sciences, Volume 53, Issue 180, Page(s) 91-98.||摘要:||
This paper focuses on flow visualization, normal force and pitch moment testing of the NASA TP-1803 strake-wing model at high attack angles. The dynamic aerocharacteristics for pitching with various reduced frequencies and two sideslip angles beta = 0 degrees and 10 degrees in the water tunnel are compared with those for static case. For alpha = 20 degrees-50 degrees, the strake/wing vortices breakdown positions occur later for beta = 10 degrees than for = 0. The value of the normal force coefficient under sideslip angle beta = 10 degrees is greater than beta = 0 degrees at high attack angles. In the pitch-down process, the aerodynamic center creates a nose-up pitching moment and the model becomes unstable compared to the static condition. As the pitch reduced frequency increases, the wing vortices sustain longer flow lines and provide more normal force during pitch-up motion. In addition, the hysteresis loop of the normal force curve is larger for higher reduced frequencies.
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