A Second Order Accurate Numerical Method for Supersonic Boundary Layer Flow Past a Compression Corner.
Abstract
The compressible and incompressible boundary layer equations are solved for laminar flow past a configuration with an interior (concave) compression region. The approach first employs conformal coordinates to map the body geometry to a flat wall, and then the boundary layer scale laws to identify the principal terms of the compressible counterpart of the Navier-Stokes equations. A Levy-Lees type transformation is identified in these coordinates to simplify the governing equations. These are then solved with a second-order accurate numerical scheme in both the longitudinal and normal directions. Solutions are obtained for adiabatic and 'warm' wall conditions for configurations with and without separation. Emphasis is placed here on achieving accurate reliable results while maintaining minimal computer time expenditure. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1979
- Accession Number
- ADA084550
Entities
People
- Bernardo Fortunato
- M. J. Werle
Organizations
- University of Cincinnati