Magnus Effect over Aerodynamic Components of Spinning Missile

نویسندگان

چکیده

Abstract To reveal the flow mechanism of Magnus effect spinning missile, field under supersonic conditions was numerically simulated based on unsteady Reynolds-time-averaged Navier–Stokes equation, and implicit dual-time stepping method sliding mesh were used. Validation performed to ensure reliability numerical methods. The results simulation wind-tunnel experimental data coincided quite well. aerodynamic characteristics various configurations while calculated. components interference between analyzed. indicate that for projectile body, canard enlarges time-averaged side force; when slenderness ratio becomes large, from view base, left leeward separation vortex is close surface, resulting in a low-pressure region, direction force yawing moment are changed. fin installation angle can weaken body some extent. For fin, influence vortices depends their relative positions. even cause reversal direction.

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ژورنال

عنوان ژورنال: International Journal of Aeronautical and Space Sciences

سال: 2022

ISSN: ['2093-274X', '2093-2480']

DOI: https://doi.org/10.1007/s42405-022-00452-9