Abstract
Based on the three-dimensional Navier–Stokes (N–S) equations, using unsteady numerical technology, flow over a dual-spin projectile was simulated to investigate its aerodynamic characteristics during flight. Spin was achieved via the sliding mesh method. The influence laws of the aftbody spin rate, Mach number, and angle of attack on the aerodynamic characteristics of the projectile are presented, and the flow mechanisms for the laws are revealed. The results demonstrate that the influence of the aftbody spin rate on the normal force coefficient is very small, whereas, on the lateral force coefficient, it is larger. With the increase in the Mach number, the time-averaged normal force coefficient and lateral force coefficient increase, while the fluctuation quantities of the normal force coefficient and the lateral force coefficient decrease. The variation of angle of attack will influence the size, distribution, and interference effect of the shedding vortices.
| Original language | English |
|---|---|
| Pages (from-to) | 4541-4553 |
| Number of pages | 13 |
| Journal | Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering |
| Volume | 233 |
| Issue number | 12 |
| DOIs | |
| Publication status | Published - 1 Sept 2019 |
Keywords
- Two-dimensional trajectory correction projectile
- aerodynamic characteristic
- dual-spin projectile
- numerical simulation
- sliding grid