Flow Simulation and Drag Components for HEAT Projectiles with Spike and Cone Noses.
Abstract
Seven computations are reported for the two classes of projectile configurations of shaped charge antitank projectiles. The first class is of spiked nose with vortex generator ring, boattail, and tail fin boom. The second is of conical nose, boattail, and tail fin boom. Navier-Stokes equations are solved for the turbulent flow with dominant separation region, in an axisymmetric formulation and for zero angle of attack. Two cases at Mach numbers 3.5 and 3.0 were computed for the spiked configuration at wind tunnel Reynolds numbers. Five cases were computed for the second configuration class. Three of these cases were made at Mach numbers 4.3, 3.95, and 2.05 at sea-level conditions for the second configuration which depicts the M830A1 projectile. The other two cases were computed at wind tunnel conditions for a 40% scaled down model of an early version of the M830A1 projectile, designated as the third configuration. The flow field is computed and analyzed, providing detailed anatomy of the drag for each configuration. Comparison was made with the few body-alone wind tunnel data. This work provides details of drag components of each part of the configurations. The present work also paves the way to complete HEAT projectile viscous modeling when tail fins are included.
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 01, 1995
- Accession Number
- ADA301924
Entities
People
- Ameer G. Mikhail
Organizations
- United States Army Research Laboratory