Multiple numerical techniques are used to investigate the effect of the location of the body bend location (varied from nose base to center-of-gravity) and the nose and body bending angles (each varied from 0° to 7.5°) on the aerodynamic performance of a bent body projectile in the supersonic regime. Each of the numerical techniques was validated for the baseline Air Force Finner (AFF) geometry. Simulations of 31 different bent body configurations using the Reynolds-Averaged Navier-Stokes (RANS) code were completed at Mach 2 and Mach 3. Some of the bent body configurations were found to obtain a trimmed condition (approximately 30% at Mach 2 and 6% at Mach 3), but most were unstable. A subset of the configurations, to include both unstable and stable configurations, was investigated in greater detail, including with an Euler code. The Euler code provided reasonable results when compared to the RANS solutions with superior efficiency. A comparison of 4 bent body configurations to the AFF with deflected canards showed that greater control authority could likely be obtained for the bent body configuration, if static stability is not considered a prerequisite.
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