Aerodynamic Investigation of a Supersonic Bending Body Projectile with Shape Optimization

Report No. ARL-TR-8797
Authors: Justin L Paul, Joseph D Vasile, Jim DeSpirito, and Sidra I Silton
Date/Pages: September 2019; 71 pages
Abstract: A Particle Swarm Optimization algorithm was implemented along with an Euler (inviscid) computational fluid dynamics code to determine both body bending angles and locations that separately optimized two parameters: lift-to-drag ratio at the trim angle of attack and pitching moment coefficient at 0° angle of attack. The Air Force Finner missile at a Mach number of 2 was used as the baseline configuration. As a constraint, only configurations that could reach a trimmed condition over the angle of attack range (-10°<α<10°) were considered valid. The performance of the Euler code was evaluated by modeling the baseline Air Force Finner and comparing with archival experimental data as well as previous high-fidelity, viscous simulations. The Euler code produced comparable solutions to the viscous solutions for multiple bending body configurations with superior efficiency. Implementation of the shape optimization resulted in convergence to a different configuration, but with similar lift-to-drag ratios and trim angles of attack, for each of the optimized parameters. A "bentness" angle was defined that had a similar value for both optimal configurations. The optimal bending body configurations produced significantly higher pitching moment increments and improved maneuverability potential over a generic canard-controlled configuration with a 10° canard deflection. A 34% increase in lift-to-drag ratio was achieved for the bending body configurations. Overall, the optimization routine proved to be an efficient tool for producing highly maneuverable aerodynamic designs.
Distribution: Approved for public release
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Last Update / Reviewed: September 1, 2019