Numerical Solution of Interacting Supersonic Boundary Layer Flows Including Separation Effects,
Abstract
An efficient numerical solution algorithm is presented for solving the interacting supersonic laminar boundary layer problem. The method employs a time dependent approach with the alternating direction implicit (ADI) scheme and directly accounts for the necessary downstream boundary condition. Solutions are presented for (M sub infinity) = 3 cold wall boundary layer flow over a family of expansion and compression ramps including several cases with regions of reverse flow. Good comparison is given with experimental data and Navier Stokes solutions for (M sub infinity) = 4, adiabatic wall, separated flow up a ten degree compression ramp. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1973
- Accession Number
- AD0777570
Entities
People
- M. J. Werle
- V. N. Vatsa
Organizations
- University of Cincinnati