PERTURBATIONS OF SIMPLE WEDGE FLOW RELATING TO AXISYMMETRIC HYPERSONIC INTAKES OR IMPLODING CYCLINDRICAL SHOCKS.
Abstract
The flow near the leading edge of a sharp-lipped, finite angle axisymmetric intake is studied within the approximations of the hypersonic small disturbance theory. The radial distance of the unperturbed shock measure inwards from the intake lip is non-dimensionalised with respect to the lip radius and this quantity taken as a small parameter tau. Solutions are obtained as series expansions to the second order in tau and the results may be applied to any shock shape, or surface shape, expressed as a series in tau without further computation. Comparisons are made with exact numerical calculations for the cases of the internal conical surface and of the internal conical shock to indicate range of application of the solutions. The results may be applied to the equivalent unsteady flow problem. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 1968
- Accession Number
- AD0674246
Entities
People
- R. F. Meyer
Organizations
- National Research Council Canada