Aerodynamic Shape Optimization for a Hollow Projectile Based on Blind Kriging

Abstract

The design for an anti-aircraft hollow projectile, provided with ample power and precision, to minimize the flight time of a given slant distance is of vital importance. With the purpose of obtaining the optimal aerodynamic shape with the shortest possible spent time of a given slant distance, combined with the application of UG, ICEM CFD and FLUENT etc softwares and script program, the corresponding drag coefficients of different aerodynamic shapes under the condition of Ma=2.5~4.0 and attack angle =0º have been obtained, and Blind Kriging surrogate model is established for the drag coefficient. By use of sequential quadratic programming method, based on point mass trajectory model, the aerodynamic shape has been optimized to minimize the flight time of some given slant distances, and the optimal aerodynamic shape has been obtained. The numerical optimal method which is proposed in this paper for optimizing the hollow projectile can provide important guidance for relative engineering application and investigations.