CFD Investigation on the Subsonic Aerodynamic Evaluation of Grid-Fin Patterns with Missile Body Configuration
摘要
The existing numerical analysis evaluates the subsonic aerodynamic characteristics of four distinct grid patterns pertaining to the unconventional control surface called ‘Grid fins,’ integrated with a missile body. To explore the effect of grid cell’s shape on aerodynamic coefficient and flow-physics of grid fins and overall vehicle, these grid fin configurations were numerically investigated at freestream Mach numbers of 0.1, 0.3 and 0.5 and varying angle of attack ranges. Solver validation pertaining to this numerical study presented a good agreement within 9.8% with respect to the referred experimental study. The research findings reveal that the square pattern minimizes axial force, lowest CA at zero-deg. α, but exhibited a strong interaction effect with highest δCA. hexagonal pattern offers balanced performance with moderate CA, lower CN, and significant δCN at mid α. diamond pattern yields the highest CN with minimal interaction effect δCA, excelling in generating normal force. triangular fin, despite minimal interaction effect with lower δCA, have high CA at zero-deg. α, reducing aerodynamic performance. Inferences drawn from the study can serve as a preliminary reference for evaluating the aerodynamic metrics of different grid fin patterns, especially in the subsonic regime.