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- W2313305231 abstract "Wind tunnel tests were performed on a vertically-launched surface-to-air missile model to investigate the effects of low-aspect-ratio strakes and wings on the side forces and yawing moments induced by nose-generated asymmetric vortices at high angles of attack. Force and moment data were collected for angles of attack from 0 to 90 deg at a Reynolds number, based on model diameter, of 1.1 x lo5, and at a Mach number of 0.1. In a second series of tests at 50 deg angle of attack, flowfield measurements were made at two crossplane locations for vortex positions and strengths. Three body configurations were tested. Induced side forces and yawing moments were found to be maintained with the addition of wings and strakes. At the onset of the asymmetric vortices, yawing moments were of opposite sign to the induced side forces, indicating the dominance of afterbody side forces. However, as side forces increased with angle of attack, the forebody vortices quickly became dominant. Velocity vector plots, total pressure loss contours, and vorticity contours all proved useful in characterizing the lee flowfield. Though the lee flowfield for the two winged configurations (0 and 45 deg roll angle) differed greatly, both maintained identical levels of yawing moment coefficient ." @default.
- W2313305231 created "2016-06-24" @default.
- W2313305231 creator A5053276098 @default.
- W2313305231 date "1990-08-17" @default.
- W2313305231 modified "2023-09-26" @default.
- W2313305231 title "Wing effects on asymmetric vortex formation for a ship-launched missile" @default.
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- W2313305231 doi "https://doi.org/10.2514/6.1990-2851" @default.
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