Anti-Tank Spike-Nosed Projectiles With Vortex Rings: Steady and Non- Steady Flow Simulations
Abstract
Numerical computations are reported for a spike-nosed projectile configuration with a vortex generator ring. A new vortex-dominated flow field is computed at supersonic speeds of M - 3.5, 3.0, and 1.9. A time-dependent Navier- Stokes computational technique with a zonal gridding was used. The axial force at zero angle of attack was computed and found to be in good agreement with the wind tunnel data at Mach 3.0. The sting quantitative effect on the axial force coefficient and the flow pattern was found to be very minor for the present case at Mach 3.5. A high drag solution for a case computed at Mach 3.5 was obtained by imposing a cross flow velocity of seven percent of the freestream velocity. This result removed any doubt that the wind tunnel results for that Mach number were for the high drag mode. An additional interesting case was computed at Mach 1.9; and the flow was found to be of the oscillator (buzzing) type. The frequency of the oscillation was computed as 5333 Hz and indicated that the designers of the projectile in 1980 were apparently not aware of the possible buzzing flow along the projectile trajectory when it decelerates from Mach 3.5 to 1.9. They had tested the projectile only at Mach 3.5 and 3.0. No tests were made at Mach 1.9 or lower.... Anti-tank projectiles, Spikes, Aerodynamic drag, Supersonic drag, Numerical integration, Axisymmetric flow, Turbulent flow, Flow field, Unsteady flow.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1993
- Accession Number
- ADA262507
Entities
People
- Ameer G. Mikhail
Organizations
- United States Army Research Laboratory