Numerical Solutions to the Full Viscous Shock Layer Equations using an Alternating Direction Implicit Technique,

摘要

Numerical solutions to the viscous shock layer equations are presented for hypersonic flow past hyperboloids opening to asymptotic total interior angles of 45degrees and 20degrees. Solutions were obtained using a modified form of the conventional alternating direction implicit approach which uses a time dependent iterative relaxation process for determining the bow shock shape. Solutions were obtained to the full shock layer equations as well as their thin shock layer approximations for Mach numbers M = 10and 21.75,free stream Reynolds numbers,Re,of 430and 64000and wall to stagnation temperature ratios of 0.05and 0.9. (Modified author abstract)