Aerodynamic Investigation of a Supersonic Bending Body Projectile with Shape Optimization
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 degt<alpha<10 deg) 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.
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 19, 2019
- Accession Number
- AD1080931
Entities
People
- Jim Despirito
- Joseph D. Vasile
- Justin L. Paul
- Sidra I. Silton
Organizations
- United States Army Research Laboratory