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- W2392471696 abstract "When a fighter aircraft or missile flies at high angle of attack(AOA),asymmetric vortexes are produced from the forebody and induce strong side force and yawing moment.In order to reduce the side force and yawing moment by controling the asymmetric vortexes,the effects of bumps on the forebodies are investigated.Tests with force measurement in a wind tunnel and with flow visualization in a water tunnel are performed.Test results show that as the angle of attack is in the range of 20°~70°,the effects of bumps on the cone-cylinder are very large,those on the elliptic section model are middle and those on the chined section model are small.When bumps are situated more closed to the tip of the forebody,the effects of bumps on the side force are stronger.The bumps on the cone cylinder model affect only on the curve shape of variatian of the side force with angle of attack and has a small effect on the maximum side force.The larger bumps on the elliptic section model are able to decrease the maximum side force coefficient from 1.98 to 0.53.The side force coefficient of the chined section model is unsensitive to both the size and the position of the bump." @default.
- W2392471696 created "2016-06-24" @default.
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- W2392471696 date "2007-01-01" @default.
- W2392471696 modified "2023-09-26" @default.
- W2392471696 title "Study of Effects of Bumps on Forebodies with Different Sections on Side Force" @default.
- W2392471696 hasPublicationYear "2007" @default.
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