The Conically Symmetric Navier Stokes Equations: Numerical Solution for Hypersonic Cone Flow at High Angle of Attack.
Abstract
Solutions were obtained for hypersonic flow over sharp cones at high angle of attack by numerically integrating through use of MacCormack's method the Navier-Stokes equations subject to a conical symmetry assumption. The boundary conditions for the integration were chosen to match experimental conditions. A technique (normal stress damping) was developed to provide damping of the numerical oscillations occurring at shock discontinuities during the integration. The general features which appeared in experiment were shown to appear in the results of the integration, including the proper behavior, in laminar flow, of the viscous layer and the vertical singularity. A thinner calculated lee side viscous layer was attributed to failure of the present technique to model non-conical nose effects. A solution obtained just upstream of boundary layer transition agreed with experiment when conically projected into the turbulent regime. The adequacy of the conical symmetry assumption is therefore indicated for the turbulent regime on conical bodies.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1977
- Accession Number
- ADA042072
Entities
People
- David S. Mcrae
Organizations
- Flight Dynamics Laboratory