Project Distribution

In this project, a numerical simulation of airflow over the NLAW weapon system is performed using ANSYS Discovery. The study aims to investigate the aerodynamic behavior and flow features around the launcher under operating conditions. The obtained results provide a better understanding of the flow field, which can support design assessment and Performance Optimization of the system.

Objectives

The main objective of this study is to analyze the airflow characteristics around the NLAW weapon system at an inlet velocity of 120 meters per second. The simulation aims to evaluate the resulting pressure distribution and aerodynamic loads on the launcher surfaces. Furthermore, the results will be used to identify critical flow regions that may affect stability, structural integrity, or overall performance of the system.

Results and Discussion

The results of this simulation demonstrate that airflow over the NLAW launcher at 120 m/s exhibits a sharp pressure drop at the nose tip, followed by low-pressure zones along the body and pressure recovery near the tail fins. Velocity fields reveal flow acceleration exceeding 150 m/s over curved surfaces, with notable separation and recirculation in the wake region. These observations indicate potential drag sources and stability concerns, guiding future aerodynamic optimizations for enhanced performance.