The Calculation of Adiabatic Laminar Boundary Layer Shock Wave Interactions in Axi-Symmetric Flow. Part II. Hollow Cylinder Flare Bodies with Spin.
Abstract
The report is concerned with developing a theoretical calculation method for the three-dimensional interaction between a laminar boundary layer and a shock wave, in the case when a constant transverse velocity is imposed, parallel to the shock plane. The phenomenon is studied on an adiabatic axi-symmetric body consisting of a hollow circular cylinder with a flare. The transverse velocity is generated by the rotation of the body about its axis of symmetry which is aligned in the main flow direction. The calculation procedure is derived from the two-dimensional integral method of Lees and Reeves. The required relationships between boundary layer integral properties are obtained from similar solutions of compressible axial flow on a rotating cylinder.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1971
- Accession Number
- AD0733164
Entities
People
- Harry P. Horton
- Jean J. Ginoux
- Roger Leblanc
Organizations
- von Kármán Institute for Fluid Dynamics