Navier-Stokes Computations for Conventional and Hollow Projectile Shapes at Transonic Velocities.
Abstract
Advanced numerical techniques for the prediction of projectile aerodynamics have been applied to standard and hollow projectile shapes. Computer codes developed for solving the time dependent Generalized Axisymmetric and 3-D Thin-Layer Navier-Stokes equations have enabled simultaneous solutions of the inviscid and viscous regions of the flow field. Transonic computations have been performed for a 6-caliber secant-ogive-cylinder-boattail projectile shape at various free stream Mach numbers. Results have been obtained showing the formation of shocks near the nose-cylinder and cylinder-boattail junctions as well as the movement of these shocks with varying free stream conditions. Surface pressure distributions and velocity profiles have been obtained and are compared with available experimental data for angle of attack, alpha = O. Additional results are shown for alpha = 2 degrees, Mach = 0.96. The General geometry capability of the present method enables computations to be performed for many unique shapes such as hollow projectiles or ring airfoils. Internal and external pressure distributions are presented for a ring airfoil shape from Mach = 0.70 through Mach = 0.90.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 1982
- Accession Number
- ADA116866
Entities
People
- Charles J. Nietubicz
Organizations
- Ballistic Research Laboratory