Accession Number : ADA116866
Title : Navier-Stokes Computations for Conventional and Hollow Projectile Shapes at Transonic Velocities.
Descriptive Note : Final rept.,
Corporate Author : ARMY BALLISTIC RESEARCH LAB ABERDEEN PROVING GROUND MD
Personal Author(s) : Nietubicz,Charles J
PDF Url : ADA116866
Report Date : Jul 1982
Pagination or Media Count : 33
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.
Descriptors : *Projectile trajectories, *Projectiles, Aerodynamic characteristics, Transonic characteristics, Transonic wind tunnels, Supersonic characteristics, Artillery, Navier Stokes equations, Velocity, Computations, Aerodynamic drag, Angle of attack
Subject Categories : Numerical Mathematics
Ammunition and Explosives
Distribution Statement : APPROVED FOR PUBLIC RELEASE