Three Dimensional Supersonic Flow Past Blunt Bodies - Numerical Methods and Computations.
Abstract
Methods for computing numerically the flow past blunted bodies of revolution travelling at supersonic speeds and at angles of attack are developed, using finite difference schemes. Results are shown for a given configuration at two supersonic Mach Numbers for which circumferential pressure distribution is given as well as the lift slope coefficient. To achieve greater computational efficiency a different method was introduced - one based on mapping the body into a line (in the 2-D case) or a rectangle. This was tested so far on the axisymmetric case. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 1977
- Accession Number
- ADA050335
Entities
People
- Saul S. Abarbanel
Organizations
- Tel Aviv University