Effect of Shape Parameters on Aerodynamic Performance of Grid Fin for Resuable Carrier Rocket

The Grid fins of resuable carrier rocket present distinct advantages over conventional control surfaces in terms of foldability, enhanced stall characteristics, and reduced hinge moments. However, the aerodynamic implications of different grid fin configurations remain insufficiently understood. This study investigates the influence of specific shape parameters on the aerodynamic performance of grid fins across a Mach range from 0.4 to 5, providing computational insights that may guide future optimization efforts. Key parameters such as aspect ratio, local leading-edge sweep angle, and split leading-edge sweep angle were selected for detailed analysis. Following the definition of these parameters, computational grids were generated through hybrid mesh generation techniques, and the aerodynamic performance of the grid fins was subsequently quantified using Reynolds-averaged Navier-Stokes (RANS) equations. The results indicate that aspect ratio significantly affects the third critical Mach number, beyond which shock waves at the grid fin's leading edge do not adversely effect adjacent structures. Additionally, the local leading-edge sweep angle can induce vortex lift at the fin's leading edge. These findings form the foundation for further aerodynamic enhancements in grid fin design.