BINARY BOUNDARY LAYERS ON SHARP CONES IN LOW DENSITY SUPERSONIC AND HYPERSONIC FLOW.
Abstract
The effects of surface mass transfer on the flow field around sharp slender cones at zero angle of attack in low density supersonic and hypersonic flow are computed using an iterative inviscid-viscous flow field calculation model. The perfect gas model which is developed considers nonsimilar binary gas boundary layers, viscous interaction, transverse curvature, wall slip, and temperature jump. The inviscid and viscous flow fields are matched using a displacement thickness that includes the effects of surface mass transfer, and the inviscid flow is computed using either the tangent cone theory or the conical shock expansion theory. Calculated effects of helium argon, carbon dioxide, and air injection on total drag values and surface pressure distributions are compared with experimental data. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 01, 1969
- Accession Number
- AD0682294
Entities
People
- Arloe W. Mayne Jr.
- Clark H. Lewis
- G. E. Gilley
Organizations
- Arnold Engineering Development Complex