SUN Hai-sheng, JIANG Yu-biao, LIU Zhi-tao, et al. Experimental research on the high angle of attack aerodynamic characteristics of an 80°/65° double-delta wing[J]. Journal of Experiments in Fluid Mechanics, 2011, 25(6): 6-12. doi: 10.3969/j.issn.1672-9897.2011.06.002
Citation:
SUN Hai-sheng, JIANG Yu-biao, LIU Zhi-tao, et al. Experimental research on the high angle of attack aerodynamic characteristics of an 80°/65° double-delta wing[J]. Journal of Experiments in Fluid Mechanics, 2011, 25(6): 6-12. doi: 10.3969/j.issn.1672-9897.2011.06.002
SUN Hai-sheng, JIANG Yu-biao, LIU Zhi-tao, et al. Experimental research on the high angle of attack aerodynamic characteristics of an 80°/65° double-delta wing[J]. Journal of Experiments in Fluid Mechanics, 2011, 25(6): 6-12. doi: 10.3969/j.issn.1672-9897.2011.06.002
Citation:
SUN Hai-sheng, JIANG Yu-biao, LIU Zhi-tao, et al. Experimental research on the high angle of attack aerodynamic characteristics of an 80°/65° double-delta wing[J]. Journal of Experiments in Fluid Mechanics, 2011, 25(6): 6-12. doi: 10.3969/j.issn.1672-9897.2011.06.002
The aerodynamic characteristics,pressure distribution and flowfield evolution of an 80°/65° double-delta wing model have been studied in φ3.2m low speed wind tunnel at CARDC by means of force measurement,pressure measurement and PIV technique.The Reynolds number is 0.49~1.3( × 106)and the range of angle of attack(AoA) is between 0° and 60°.The study indicates that the results obtained from different types of tests have good correlation.The lift coefficient reaches maximum at 30° AoA,changes slightly between 30°~37° AoA,then drops rapidly as AoA increases.When AoA exceeds 30°,the leading edge vortex begins to break down.From 38° to 40° AoA,the suctionpeak disappears gradually and pressure coefficient decreases evidently.After 40° AoA,the suction peak disappears completely and leading edge vortex breaks down totally.
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