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• W2063757208 abstract "Force, surface pressure, and e owe eld measurements were made on a 0.5-m root chord, 70-deg delta wing model with leading-edge vortex e aps at the National Aerospace Laboratory, Japan. The main objective of the experiment is to investigate the effect of the wing sweepback angle upon the vortex e ap performance. Improvements in the lift/drag ratio were observed in a 70-deg delta wing by dee ecting the tapered vortex e aps. Comparisons between the previously measured 60-deg delta wing results and the present results were made. The improvements in the lift/drag ratio of the 70-deg delta wing were attained over a narrower lift coefe cient range than for the 60-deg delta wing. The results also showed that the maximum lift/drag ratio for the 70-deg delta wing is attained when the spanwise length of the separated region formed on the vortex e ap surface almost coincides with the e ap span." @default.
• W2063757208 created "2016-06-24" @default.
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• W2063757208 date "1997-09-01" @default.
• W2063757208 modified "2023-10-03" @default.
• W2063757208 title "Experimental Studies of a 70-Degree Delta Wing with Vortex Flaps" @default.
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• W2063757208 doi "https://doi.org/10.2514/2.2235" @default.
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