Abstract
A preliminary investigation into the interaction of a local protuberance with a fin on a supersonic projectile has been completed. Computational fluid dynamics have been utilised throughout. A model has been computed for Mach numbers between 1.5 and 4 and between 0° and 8° angle of attack. Validation of the results has been undertaken quantitatively through comparing normal force and pitching moment coefficients to those predicted by MISL3 and NEARZEUS and experimental pressure coefficients, and qualitatively by comparing flow features to existing research. Analysis indicates the effect the protuberance has upon the flow. Boundary layer separation occurs ahead of the protuberance, leading to a shockwave which impinges upon the neighbouring fin surfaces. At angles of attack, a weaker shock forms. This affects the projectile by inducing less force upon it, thereby altering the trim angle and resulting lateral acceleration.
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