A Theoretical and Experimental Investigation of a Transonic Projectile Flow Field
Abstract
The transonic flow field about a secant-ogive-cylinder-boattail with a turbulent boundary layer has been studied. A joint theoretical and experimental effort is presented which compares the results of a generalized axisymmetric Navier-Stokes code, a composite inviscid boundary-layer/shock interaction solution method, and experiment. The experimental longitudinal pressure distribution at M= 0.94, and 0.97 for alpha = 0.0 degree are generally well predicted by both theoretical techniques although the Navier-Stokes solutions are shown to be superior in describing the detail, such as, upstream effects of expansion corners and the position and magnitude of minimum pressure regions. Both theoretical solutions predict the boundary layer velocity profiles very well in all cases with the largest differences occurring just downstream of the boattail corner. Comparisons of displacement thickness and skin friction distributions are also presented.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 1983
- Accession Number
- ADA131938
Entities
People
- Charles J. Nietubicz
- George R. Inger
- James E. Danberg
Organizations
- Ballistic Research Laboratory