Static and Dynamic Aerocharacteristics Testing of Strake-Wing Aerial Vehicle in Water Tunnel

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  • CHANG Li-Min
    Department of Mechanical Engineering, National Chung-Hsing University
  • LEE Hsing-Juin
    Department of Mechanical Engineering, National Chung-Hsing University
  • HUANG Chien-Min
    Aeronautical Systems Research Division, Chung-Shan Institute of Science and Technology
  • CHUANG Shu-Hao
    Department of Mechanical Engineering, National Chung-Hsing University
  • WANG Shu-Wei
    Department of Mechanical Engineering, National Chung-Hsing University
  • CHIEN Kuo-Tung
    Aerospace Industrial Development Corp.

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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 β=0° and 10° in the water tunnel are compared with those for static case. For α=20°–50°, the strake/wing vortices breakdown positions occur later for β=10° than for β=0°. The value of the normal force coefficient under sideslip angle β=10° is greater than β=0° 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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