| ID | 136039 |
| Title Proper | Flow around a conical nose with rounded tail projectile for subsonic, transonic, and supersonic flow regimes |
| Other Title Information | a numerical study |
| Language | ENG |
| Author | Kumar, Amitesh ; Panda, H S ; Biswal, T K ; Appavuraj, R |
| Summary / Abstract (Note) | Flow around a conical nose with rounded tail projectile has been studied numerically for subsonic, transonic and supersonic flow regimes. The conic angle of the projectile is 10°. The inflow Mach numbers are 0.5, 0.9, and 1.5. Axisymmetric Euler’s equations are solved for predicting the drag coefficient. It has been observed that even for a subsonic flow regime, the Mach number distribution is not uniform owing to the non-symmetric shape of the projectile. The predicted drag coefficients for subsonic, transonic, and supersonic cases are 0.018, 0.089, and 0.395, respectively. It was observed that rounded tail is a better option than boat tail so far drag force is concerned. |
| `In' analytical Note | Defence Science Journal Vol.64, No.6; Nov.2014: p.509-516 |
| Journal Source | Defence Science Journal 2014-12 64, 6 |
| Key Words | Numerical Modeling ; Projectile ; Drag ; Supersonic Flow ; Nose Angle ; Subsonic Flow Regime |