Optimization of the aerodynamic configuration of a tubular projectile based on blind kriging

Abstract

Based on optimal Latin hypercube design of computer experiments, blind kriging surrogate model, and sequential quadratic programming method, the optimal design of the aerodynamic configuration of a 30 mm tubular projectile is carried out through commercial software products such as UG, ICEM CFD, FLUENT, etc. The aerodynamic configuration has been optimized to minimize the drag coefficients at different Mach numbers and maximize the kinetic energies at given flight ranges. The optimal configuration is obtained and discussed. Finally, the similarities and differences of the flow structure and aerodynamic characteristics between the original and optimal tubular projectiles are compared. The numerical optimal method proposed in this paper for optimizing the tubular projectile can provide important guidances for the aerodynamic configuration design of projectiles.