Numerical Solution of the Conically Symmetric Navier-Stokes Equations for Hypersonic Cone Flow at 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 the experiment conditions of Tracy (M=7.95), Stetson (M=14.2), and McElderry (M=6.05). 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 vortical singularity. The results agreed quite well with the experimental data of Tracy and agreed less with the experiment data of Stetson. A thinner calculated lee side viscous layer for Stetson's case was attributed to failure of the present technique to model non- conical nose effects. A solution obtained just upstream of boundary layer transition at the experimentalal conditions of McElderry 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
- Jul 01, 1976
- Accession Number
- ADA028351
Entities
People
- David S. Mcrae
Organizations
- Air Force Institute of Technology