The Calculation of Adiabatic Laminar Boundary Layer Shock Wave Interactions in Axi-Symmetric Flow. Part I. Hollow Cylinder-Flare Bodies with Zero Spin.
Abstract
A method is described for calculating the overall properties of flare-induced laminar boundary layer shock wave interactions on axi-symmetric bodies at zero incidence, under adiabatic conditions. The method consists of an extension to axi-symmetric flow of the two-dimensional integral boundary layer method of Lees and Reeves, in the improved form recently developed by Klineberg. The relationship between the local slope of the displacement surface and the external Mach number is calculated by a suitable inversion of the second-order shock-expansion method of Syvertson and Dennis. Satisfactory agreement is demonstrated between the theory and measurements on hollow cylinder-flare models at Mach numbers of 2.2 and 4.0. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- May 01, 1970
- Accession Number
- AD0873051
Entities
People
- Harry P. Horton
Organizations
- von Kármán Institute for Fluid Dynamics